25th week of 2017 patent applcation highlights part 36 |
Patent application number | Title | Published |
20170175557 | GAS TURBINE SEALING - A gas turbine having a seal sealing a trench cavity defined between a stator inboard face and rotor inboard face. The seal may include a stator overhang that extends axially toward the rotor inboard face. The stator overhang may include an overhang topside, an overhang underside, and an overhang face that is defined therebetween. The trench cavity seal may include a platform lip extending axially from the rotor inboard face toward the stator inboard face and circumferentially spaced turbulators extending axially from the rotor inboard face. An outboard edge and an inboard edge of the stator overhang axially jut such that, therebetween, a recessed pocket on the overhang face is formed. The platform lip may radially overlaps the recessed pocket on the overhang face so to form a multiple switch-back flowpath. | 2017-06-22 |
20170175558 | HULA SEAL - A hula seal as disclosed extends in a circumferential direction, a radial direction and an axial direction relative to a central axis. The hula seal includes a first leaf extending from the first edge region to the second edge region and a second leaf extending from the first edge region to the second edge region. The first leaf is the same distance as the second leaf from the central axis in the radial direction, and is adjacent to and overlaps the second leaf in the circumferential direction, when installed in a gas turbine. The first leaf is attached to the second leaf such that the first leaf can move relative to the second leaf in the circumferential direction when installed in a gas turbine. | 2017-06-22 |
20170175559 | BLADE OUTER AIR SEAL WITH INTEGRATED AIR SHIELD - A blade outer air seal according to an example of the present disclosure includes a seal body extending circumferentially about an axis and including at least one channel having a substantially solid radially outer surface. A substrate is radially inward of the at least one channel with respect to the axis. The substrate and the at least one channel form at least one cavity. A rotor rub strip is radially inward of the substrate. | 2017-06-22 |
20170175560 | TURBINE ABRADABLE LAYER WITH AIRFLOW DIRECTING PIXELATED SURFACE FEATURE PATTERNS - A turbine abradable component includes a support surface and a thermally sprayed ceramic/metallic abradable substrate coupled to the support surface for orientation proximal a rotating turbine blade tip circumferential swept path. An elongated pixelated major planform pattern (PMPP) of a plurality of discontinuous micro surface features (MSF) project from the substrate surface. The PMPP repeats radially along the swept path in the blade tip rotational direction, for selectively directing airflow between the blade tip and the substrate surface. Each MSF is defined by a pair of first opposed lateral walls defining a width, length and height that occupy a volume envelope of 1-12 cubic millimeters. The PMPP arrays of MSFs provide airflow control of hot gasses in the gap between the abradable surface and the blade tip with smaller potential rubbing surface area than solid projecting ribs with similar planform profiles. | 2017-06-22 |
20170175561 | METHOD OF SIZING A CAVITY IN A PART - A method of sizing a cavity in a part and a part made from such method. The method includes forming the part having the cavity, including forming a plurality of protrusions extending within the cavity from at least one internal surface of the cavity, the protrusions having distal ends bordering an unobstructed portion of the cavity, the unobstructed portion having an initial dimension at least partially defined by a position of the distal ends, pressing a deforming element against the distal ends of the protrusions to plastically deform the protrusions toward the at least one internal surface of the cavity and increase the initial dimension to a final dimension, and disengaging the deforming element from the distal ends. | 2017-06-22 |
20170175562 | DEVICE FOR CONTROLLING CLEARANCE AT THE TOPS OF TURBINE ROTATING BLADES - A device for controlling clearance at the tops of turbine rotating blades. The device comprises shroud supporting rings, abradable ring sectors, elastic centering means, and a shroud supporting ring sectors inserted radially to the supporting shroud, between the elastic means and the abradable ring sectors, which are attached to said supporting shroud, which has a volume varying according to temperature, due to the action of fluid supply means. | 2017-06-22 |
20170175563 | MANIFOLD FOR USE IN A CLEARANCE CONTROL SYSTEM AND METHOD OF MANUFACTURING - A manifold for use in a clearance control system is provided. The clearance control system includes a housing including a plurality of walls that at least partially define an interior of the housing, and a nozzle portion integrally formed with the housing. The nozzle portion extends between adjacent walls of the plurality of walls and including at least one nozzle projection having a plurality of impingement openings defined therethrough. The at least one nozzle projection extends from the adjacent walls in an outward direction relative to the interior of the housing. | 2017-06-22 |
20170175564 | Flywheel with Inner Turbine, Intermediate Compressor, and Outer Array of Magnets - A flywheel is provided in combination with a hybrid machine, wherein said flywheel comprises, in a radial direction, from inward to outward, an inner turbine, an intermediate compressor, and an outer array of magnets. The turbine cooperates with said hybrid machine to spin faster when said machine decelerates, and slower when said machine accelerates. An inner turbine drives both said intermediate compressor and said hybrid machine. The outer array of magnets is driven by said hybrid machine to accelerate the flywheel to accelerate the flywheel during braking of said hybrid machine. Said hybrid machine communicates with said flywheel to house it and render energy from it, in a hybrid manner such that energy is stored in a pressure or electrical storage mode, or both pressure and electrical storage mode, to effect a regenerative mode that attains low fuel consumption. | 2017-06-22 |
20170175565 | Hybrid Propulsion System - An aeronautical propulsion system includes a fan having a plurality of fan blades and an electric motor drivingly connected to the fan for rotating the plurality of fan blades. A chemically rechargeable ultra-capacitor is included for providing the electric motor with a substantially continuous flow of electric energy during operation of the chemically rechargeable ultra-capacitor, resulting in a more efficient aeronautical propulsion system. | 2017-06-22 |
20170175566 | SYSTEMS AND METHODS FOR MONITORING COMPONENTS IN TURBOMACHINES - Systems for monitoring a component in a turbomachine can include a strain sensor comprising at least two reference points disposed on a surface of the component, and a data acquisition device connected to the turbomachine comprising a field of view, wherein the field of view is positioned to at least periodically capture the strain sensor on the component. | 2017-06-22 |
20170175567 | MODEL-BASED PERFORMANCE ESTIMATION - A controller includes a processor and memory. The memory stores instructions that, when executed, are configured to cause the processor to receive measurements pertaining to a measured operation parameter of at least a portion of a turbine system. The instructions are also configured to cause the processor to generate a customized model for the at least the portion of the turbine system. Moreover, the instructions are configured to cause the processor to estimate an estimated value using the received measurements. The estimated value pertains to a parameter of the turbine system. Furthermore, the instructions are configured to cause the processor to using the customized model, reduce or remove at least some environmental conditions from a corrected estimated value derived from the estimated value. | 2017-06-22 |
20170175568 | Acoustic Cleaning of Gas Turbine Engine Components - The present disclosure is directed to a method for cleaning gas turbine engine components using an acoustic emitter. More specifically, in one embodiment, the method includes positioning the acoustic emitter at a cleaning location of a component of the gas turbine engine. For example, the cleaning location is typically characterized by having a build-up of foulants on a surface thereof. Thus, the method includes emitting, via the acoustic emitter, acoustic waves at a predetermined frequency towards the cleaning location of the component so as to disperse the foulants. | 2017-06-22 |
20170175569 | System and Method for In Situ Cleaning of Internal Components of a Gas Turbine Engine and a Related Plug Assembly - A system for in situ cleaning of internal components of a gas turbine engine may generally include a plug assembly defining a fluid passageway that is configured to be installed within an access port of the engine such that the fluid passageway defines a flow path between inner and outer casings of the engine. The plug assembly may include an inner sleeve at least partially defining the fluid passageway and an outer sleeve configured to receive a portion of the inner sleeve. The system may also include a fluid conduit configured to be coupled between a fluid source positioned external to the gas turbine engine and an inlet end of the plug assembly for supplying a cleaning fluid to the plug assembly. The cleaning fluid may be directed through the fluid passageway and may then be expelled from the plug assembly into the interior of the gas turbine engine. | 2017-06-22 |
20170175570 | SYSTEMS AND METHODS FOR COATING A COMPONENT - A system for coating a component is provided. The system includes a feedstock supply, a carrier fluid supply, and a thermal spray gun coupled in flow communication with the feedstock supply and the carrier fluid supply. The feedstock supply contains a substantially homogeneous powder mixture of a first powder and a second powder. The second powder is softer than the first powder and has a percentage by mass of the powder mixture of between about 0.1% and about 3.0%. | 2017-06-22 |
20170175571 | METHOD OF MANUFACTURING A METAL MATRIX REINFORCED COMPOSITE COMPONENT AND A COMPOSITE COMPONENT FORMED BY THE METHOD - Method of manufacturing a metal matrix composite component includes the steps of providing a first tubular member having a first end and an opposite second end, the first tubular member's first end being formed as a first end block; positioning a metal matrix composite tubular member concentrically the first tubular member; positioning a second tubular member concentrically over metal matrix composite tubular member, second tubular member having a first end and an opposite second end, the second tubular member's second end being formed as a second end block; welding first tubular member's first end to the second tubular member's first end, and the first tubular member's second end to second tubular member's second end, to join the first and second tubular member and thereby to form a metal matrix composite preform; and consolidating metal matrix composite preform by a hot isostatic pressing process to form the metal matrix composite component. | 2017-06-22 |
20170175572 | SEAL SEGMENT LOW PRESSURE COOLING PROTECTION SYSTEM - A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling flow inserts direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine. | 2017-06-22 |
20170175573 | SYSTEM AND METHOD FOR COOLING TURBINE SHROUD TRAILING EDGE - A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction. | 2017-06-22 |
20170175574 | METHOD FOR METERING MICRO-CHANNEL CIRCUIT - A shroud segment for use in gas turbines, includes a body, leading edge, trailing edge, a first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side of the lateral sides interface with a cavity having a cooling fluid. A second lateral side interfaces with a hot gas flow path. A first channel disposed within the body includes a first and second end portion. A second channel is disposed within the body includes a third and fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The first and fourth end portion have hook-shaped portions with free ends having a width greater than an adjacent portion coupled to the free end. | 2017-06-22 |
20170175575 | SEGMENTED MICRO-CHANNEL FOR IMPROVED FLOW - A system includes a shroud segment for use in a turbine and includes a body having a leading and trailing edge, first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side interfaces with a cavity having a cooling fluid. A first channel includes a first and second end portion. A second channel includes a third end portion and a fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The second end portion includes a first segmented channel with first metering feature and the third end portion includes a second segmented channel with second exit feature. The first and second exit features meter a flow of the cooling fluid within the first and second channels. | 2017-06-22 |
20170175576 | SYSTEM AND METHOD FOR UTILIZING TARGET FEATURES IN FORMING INLET PASSAGES IN MICRO-CHANNEL CIRCUIT - A shroud segment for use in gas turbines, includes a body, leading edge, trailing edge, a first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side of the lateral sides interface with a cavity having a cooling fluid. A second lateral side interfaces with a hot gas flow path. A first channel disposed within the body includes a first and second end portion. A second channel is disposed within the body includes a third and fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The first and fourth end portion have portions with free ends having a width greater than an adjacent portion coupled to the free end. | 2017-06-22 |
20170175577 | SYSTEMS AND METHODS FOR INCREASING HEAT TRANSFER USING AT LEAST ONE BAFFLE IN AN IMPINGEMENT CHAMBER OF A NOZZLE IN A TURBINE - A nozzle for a turbine is disclosed. The nozzle includes a shell, an orifice plate disposed adjacent to the shell, an impingement chamber formed between the shell and the orifice plate, and at least one baffle extending from the orifice plate into the impingement chamber to push a flow of cooling fluid into the shell. | 2017-06-22 |
20170175578 | IMPINGEMENT COOLING BAFFLE - A component for a gas turbine engine includes a first component end, a second component end and a cavity extending from the first component end to the second component end. A baffle assembly is located in the cavity including a first baffle portion inserted into the cavity and a second baffle portion inserted into the cavity. The first baffle portion overlaps the second baffle portion. A vane for a gas turbine engine includes an outer platform, an inner platform and an airfoil portion extending. A core extends through the airfoil portion. A baffle is positioned in the core and is offset from the core wall. The baffle includes a first baffle portion inserted into the core and a second baffle portion inserted into the core. One of the first baffle portion or the second baffle portion overlaps the other of the first baffle portion or the second baffle portion. | 2017-06-22 |
20170175579 | HEAT EXCHANGE SYSTEM FOR A POWER GEAR BOX, A POWER GEAR BOX AND A TURBO ENGINE WITH A POWER GEAR BOX - A heat exchange system for a power gear box mechanically coupling at least one low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box and the casing and/or the heat transfer device comprise at least one heat transfer and/or fluid flow guiding structure, in particular a ribbed surface, a finned surface and/or a studded surface, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box. | 2017-06-22 |
20170175580 | SYSTEM AND METHOD FOR COOLING TURBINE SHROUD - A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes a first channel disposed within the body having a first end portion and a second end portion and a second channel disposed within the body having a third end portion and a fourth end portion. The first and second channels are configured to receive the cooling fluid from the cavity to cool the body. The first end portion and the fourth end portion each include a hook-shaped portion having a free end. | 2017-06-22 |
20170175581 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness. | 2017-06-22 |
20170175582 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft. The fan shaft support defines a fan shaft support transverse stiffness. A gear system connected to the fan shaft includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness. A flexible support supports said gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness. | 2017-06-22 |
20170175583 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support supporting the fan shaft. A gear system connected to the fan shaft includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness, and a gear mesh transverse stiffness. The gear system also includes a reduction ratio greater than 2.3. A gear system input to the gear system defines a gear system input lateral stiffness. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness and the gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness. | 2017-06-22 |
20170175584 | AERO ENGINE ROTOR AIR FLOATATION ASSEMBLING METHOD AND DEVICE BASED ON GANTRY STRUCTURE - An aero engine rotor air floatation assembling method and device based on a gantry structure belong to mechanical assembling technology. The present invention can effectively solve the problem of poor coaxality after the aero engine rotor is assembled and has the characteristics of high coaxality after the rotor is assembled, reduced vibration, mounting easiness, high flexibility and improved engine performance. The measuring method and device are: determining rotary reference based on a rotary air bearing; determining the angular positioning of a rotary table according to a grating ruler; extracting the radial error of the radial mounting plane and the inclination error of the axial mounting plane of the rotor based on the four-probe measuring device to obtain the influencing weight of this rotor to the assembled rotor on coaxality; measuring respectively all the rotors required for assembling to obtain the influencing weight of each rotor to the assembled rotor on coaxality; vector optimizing the weight of each rotor to obtain the assembling angle of each rotor. | 2017-06-22 |
20170175585 | METHOD AND INSTALLATION FOR STORING AND RECOVERING ENERGY - The invention relates to a method for storing and recovering energy, according to which a condensed air product (LAIR) is formed in an energy storage period, and in an energy recovery period, a pressure flow is formed and is expanded to produce energy using at least part of the condensed air product (LAIR) without a supply of heat from an external heat source. The method comprises inter alia, for the formation of the condensed air product (LAIR): the compression of air (AIR) in an air conditioning unit ( | 2017-06-22 |
20170175586 | FLOW AND PRESSURE ESTIMATORS IN A WASTE HEAT RECOVERY SYSTEM - An apparatus includes a pump circuit structured to receive pump data indicative of an operating characteristic of a pump feeding a fluid to a waste heat recovery (WHR) system; a flow circuit structured to receive valve position data indicative of a position of a valve downstream of the pump, estimate a flow rate of the fluid exiting the pump, and estimate the flow rate of the fluid exiting the valve; and a pressure circuit structured to receive pressure data indicative of the pressure of the fluid exiting the valve, estimate a change in pressure of the fluid across the WHR system, and determine a pressure of the fluid in a hot section of the WHR system based on the pressure of the fluid exiting the valve and the change in the pressure of the fluid across the WHR system. | 2017-06-22 |
20170175587 | RANKINE CYCLE SYSTEM FOR VEHICLE - A Rankine cycle system includes a boiler configured to apply waste heat to refrigerant circulating in an internal-combustion engine to vaporize the refrigerant; a gas-liquid separator configured to separate gas-liquid two-phase refrigerant, sent from the boiler, into gas phase fluid and liquid phase fluid; a superheater configured to superheat the gas phase fluid, sent from the gas-liquid separator, through heat exchange with exhaust gas of the internal-combustion engine; an expander configured to expand the gas phase fluid, passing through the superheater, to recover thermal energy, and a condenser configured to condense the gas phase fluid, passing through the expander, to return the gas phase fluid to liquid phase fluid. The gas-liquid separator is fixed to a cylinder head of the internal-combustion engine. It is preferable that the gas-liquid separator is configured to include a bracket, and is fixed to the cylinder head via the bracket. | 2017-06-22 |
20170175588 | RANKINE CYCLE SYSTEM FOR VEHICLE - A Rankine cycle system includes a boiler configured to apply waste heat to refrigerant circulating in an internal-combustion engine to vaporize the refrigerant; a gas-liquid separator configured to separate gas-liquid two-phase refrigerant, sent from the boiler, into gas phase fluid and liquid phase fluid; a superheater configured to superheat the gas phase fluid, sent from the gas-liquid separator, through heat exchange with exhaust gas of the internal-combustion engine; an expander configured to expand the gas phase fluid, passing through the superheater, to recover thermal energy, and a condenser configured to condense the gas phase fluid, passing through the expander, to return the gas phase fluid to liquid phase fluid. The gas-liquid separator is connected to the internal combustion engine via a refrigerant pipe. The internal combustion engine is fixed onto an engine mount of a vehicle. The gas-liquid separator is fixed to the internal combustion engine via a bracket. | 2017-06-22 |
20170175589 | CONDENSING HEAT RECOVERY STEAM GENERATOR - A condensing heat recovery steam generator (cHRSG) includes a main stack for an exhaust hot gas main flow, a bypass stack for allowing a fraction of exhaust hot gas to bypass the exhaust hot gas main flow, and a heat pump. The cHRSG includes a primary water circuit, a secondary water circuit, and a tertiary water circuit. The cHRSG additionally includes a feedwater line, a first heat exchanger for providing heat exchange between the feedwater line and the secondary water circuit, and a second heat exchanger for providing heat exchange between the primary water circuit and the tertiary water circuit. In the cHRSG, latent heat is partially recovered from said exhaust hot gas circulating in the bypass stack through the second heat exchanger and additional heat is extracted in the tertiary water circuit by said heat pump, contributing to a preheating performed in a preheater of the primary water circuit. | 2017-06-22 |
20170175590 | METHOD FOR COUPLING A STEAM TURBINE AND A GAS TURBINE AT A DESIRED DIFFERENTIAL ANGLE - A method for coupling a rotational device, particularly a steam turbine, and a shaft device, particularly a gas turbine, the method including the following steps: accelerating the rotational device up to an output rotational speed that is below the rotational speed of the shaft device; detecting a differential angle between the shaft device and the rotational device; and accelerating the rotational device with an acceleration value that is derived from the target rotational speed difference, which is formed as a function of the detected differential angle, the acceleration and a desired target coupling angle. An associated arrangement couples a rotational device. | 2017-06-22 |
20170175591 | CAM FOLLOWER ROLLER DEVICE - The cam follower roller device provides a tappet body, a pin and a roller mounted on the pin. The tappet body provides holes for mounting pin ends of the pin on the tappet body. The device further provides one deformable ring disposed between each pin end of the pin and an inner wall of the associated hole of the tappet body. | 2017-06-22 |
20170175592 | SYSTEM AND METHOD FOR VARIABLE ACTUATION OF A VALVE OF AN INTERNALCOMBUSTION ENGINE, WITH AN ELECTRICALLY OPERATED CONTROL VALVE HAVING AN IMPROVED CONTROL - A system for variable actuation of an engine valve of an engine includes a master piston driven by a cam of a camshaft. A slave piston is driven by the master piston by a volume of pressurized fluid. The slave piston causes the engine valve to open, against the action of a spring. A control valve controls a communication between pressurized fluid and an environment at lower pressure, with which a fluid accumulator is in communication. A control unit is programmed for controlling the control valve according to one or more different valve modes. When one of these valve modes is actuated, the control valve opens the communication in advance with respect to the end of the lift cycle of the cam, and not after closing of the engine valve to prevent or reduce a decrease in pressure in the volume of pressurized fluid after closing of the engine valve. | 2017-06-22 |
20170175593 | VALVE OPENING AND CLOSING TIMING CONTROL APPARATUS - A valve opening and closing timing control apparatus includes: a driving side rotor synchronously rotating with a crankshaft of an internal combustion engine; a driven side rotor disposed coaxially with a rotary axis of the driving side rotor and synchronously rotating with a camshaft; a connecting bolt disposed coaxially with the rotary axis, and connecting the driven side rotor to the camshaft; and a position determination unit performing positioning between the driven side rotor and the camshaft, or in a case where an intermediate member is provided between the driven side rotor and the camshaft, between the driven side rotor and the intermediate member, or between the camshaft and the intermediate member, wherein the position determination unit includes an engaging pin, first and second hole portions, and a deformation absorbing unit. | 2017-06-22 |
20170175594 | METHOD AND SYSTEM FOR VARIABLE CAM TIMING DEVICE - Methods and systems are described for an engine with a cam torque actuated variable cam timing phaser. Phaser positioning control is improved by reducing inaccuracies resulting from inadvertent spool valve and/or phaser movement when the spool valve is commanded between regions. In addition, improved spool valve mapping is used to render phaser commands more consistent and robust. | 2017-06-22 |
20170175595 | MULTI-POSITIONAL CAMSHAFT PHASER WITH TWO ONE-WAY WEDGE CLUTCHES AND SPRING ACTUATOR - A camshaft phaser including a gear arranged to receive torque from an engine, a housing non-rotatably connected to the gear and arranged to connect to a camshaft and a phase adjustment assembly including first gear teeth, second gear teeth and a hub arranged to non-rotatably connect to the camshaft and including third gear teeth and a displacement assembly arranged to for an advance mode, displace the hub in a first axial direction so that the third gear teeth non-rotatably connect to the second gear teeth and the hub is rotatable with respect to the housing in a first circumferential direction and for a retard mode, displace the hub in a second axial direction, opposite the first axial direction, so that the third gear teeth non-rotatably connect to the first gear teeth and the hub is rotatable with respect to the housing in a second circumferential direction. | 2017-06-22 |
20170175596 | VALVE SEAT INSERT FOR INTERNAL COMBUSTION ENGINE HAVING EXCELLENT WEAR RESISTANCE - Provided is a valve seat insert made of an iron-base sintered alloy, in which a base matrix part that includes a base matrix phase and hard particles, has a base matrix part composition containing, in % by mass, 0.5%-2.0% of carbon and 10%-70% in total of one kind or two or more kinds selected from nickel, cobalt, chromium, molybdenum, vanadium, tungsten, manganese, silicon and sulfur, with the balance being iron and unavoidable impurities, and Co-base hard particles having a composition containing, 1.0% or less of C, 25%-50% of Mo, 5%-15% of Cr, Si as an impurity in a content adjusted to be 0.3% or less, with the balance being Co, and having a Vickers hardness of 500 to 1,500 HV, are dispersed as hard particles in the base matrix phase in an amount of 10%-60% by mass with respect to the total amount of the valve seat insert. | 2017-06-22 |
20170175597 | ROCKER ARM ASSEMBLY FOR ENGINE BRAKING - An exhaust valve rocker arm assembly operable in a combustion engine mode and an engine braking mode can include a rocker shaft and a rocker arm. The rocker shaft can define a pressurized oil supply conduit. The rocker arm can receive the rocker shaft and is configured to rotate around the rocker shaft. The rocker arm can have an oil supply passage defined therein. A valve bridge can engage a first exhaust valve and a second exhaust valve. In the engine braking mode, pressurized oil is communicated through the pressurized oil supply conduit, through the rocker arm oil supply passage and against an actuator such that a first plunger acts on the valve bridge during rotation of the rocker arm to a first angle opening the first valve a predetermined distance while the second valve remains closed. | 2017-06-22 |
20170175598 | INTERNAL COMBUSTION ENGINE HAVING AN ENGINE BACKPRESSURE BRAKE AND A COMPRESSION RELEASE ENGINE BRAKE - An internal combustion engine having at least one outlet valve per cylinder, which can be actuated via a camshaft and a transmission device, a hydraulic valve clearance compensation element being arranged in the transmission device between the camshaft and the outlet valve, and having an engine braking device, having an engine backpressure brake for building up an exhaust gas backpressure and a compression release engine brake, by way of which at least one outlet valve can be held open at least in an engine braking phase, the compression release engine brake being formed by the hydraulic valve clearance compensation element. | 2017-06-22 |
20170175599 | OIL BYPASS STRUCTURE OF OIL COOLER - An oil bypass structure of an oil cooler includes: a bypass passage; an outlet side passage; and bypass valve disposed at a connection portion between the bypass passage and the outlet side passage, the bypass valve which includes a valve element including an inside passage, and within which the oil flows, the bypass valve being arranged to be closed to shut off a flow of the oil from the bypass passage to the outlet side passage by the valve element so that the oil passing through the heat exchange section flows within the inside passage, and to be opened to connect the bypass passage and the inside passage so that the oil passing through the bypass passage flows within the inside passage. | 2017-06-22 |
20170175600 | LUBRICANT COMPOSITIONS FOR SURFACE FINISHING OF MATERIALS - Described herein are lubricant compositions that include combinations of lubricant additives that are effective at improving the surface finish of a range of manufactured materials and equipment. In particular, friction modifiers and antiwear additives are employed to decrease surface roughness of additive manufactured (AM), e.g., 3D printed, materials and equipment in concert with maximizing energy efficiency. | 2017-06-22 |
20170175601 | OIL SEPARATOR - An oil separator includes: a collecting member that collects an oil mist included in blow-by gas of an internal combustion engine; and an oil separator portion inside which the collecting member is disposed, in which the collecting member includes a plurality of wire net members stacked along a flow direction of the blow-by gas. | 2017-06-22 |
20170175602 | ACTIVE NOISE CONTROL SYSTEM - A system includes an Active Noise Control (ANC) module unit configured to be installed within an air intake or exhaust of a power generation unit. The ANC module unit includes an ANC housing shaped to fit within the air intake or exhaust, an ANC core configured to be secured within the ANC housing, which includes a microphone configured to detect a sound generated by the power generation unit, a control board configured to control the noise-canceling sound based on the sound signal from the microphone and a set of pre-determined noise reduction transfer functions, and a first speaker configured to deliver a first noise-canceling sound to the air intake or exhaust. | 2017-06-22 |
20170175603 | Exhaust After-treatment System Including Electrolysis Generated H2 And NH3 - An exhaust after-treatment system including an exhaust passage, a lean-NOx trap (LNT) provided in the exhaust passage, a tank carrying an aqueous reagent, an electrochemical cell in communication with the tank and configured to receive the aqueous reagent therefrom, the electrochemical cell configured to convert the aqueous reagent into a hydrogen exhaust treatment fluid for purging the LNT, and a controller in communication with the electrochemical cell, wherein the controller is configured to vary an amount of the hydrogen exhaust treatment fluid produced by the electrochemical cell. | 2017-06-22 |
20170175604 | SYSTEM AND METHOD TO IMPROVE NOX CONVERSION FROM A HYBRID POWER PLANT - A system includes a nitrous oxide (NOx) conversion system configured to treat emissions from a conversion system, and includes a selective catalytic reduction (SCR) catalyst assembly and a temperature sensor disposed upstream of the SCR catalyst assembly to measure temperature of an exhaust before flowing into the SCR catalyst assembly. The NOx conversion system includes a temperature sensor downstream of the SCR catalyst assembly to measure a temperature of a treated exhaust flow after exiting the SCR catalyst assembly and a controller coupled to the SCR catalyst assembly. The controller receives signals representative of the temperatures to generate a first control signal representative of a desired temperature to heat the exhaust to. The controller receives the first control signal to output a second control signal to regulate a temperature of the exhaust upstream of the SCR catalyst assembly via a heating system. | 2017-06-22 |
20170175605 | EXHAUST GAS PURIFICATION SYSTEM FOR AN INTERNAL COMBUSTION ENGINE - An object of the disclosure is to adjust the ammonia adsorption amount in an SCR catalyst supported on an SCR filter as close as possible to a target adsorption amount in an exhaust gas purification system including the SCR filter. In a system according to the disclosure, the quantity of ammonia supplied by an ammonia supplier is made smaller when a differential pressure change rate at the time when ammonia is supplied by the ammonia supplier is lower than a predetermined threshold than when the differential pressure change rate at the time when ammonia is supplied by the ammonia supplier is equal to or higher than the predetermined threshold. Moreover, when the differential pressure change rate is lower than the predetermined threshold, the change in the quantity of ammonia supplied by the ammonia supplier relative to the change in the filter PM deposition amount is kept equal to zero. | 2017-06-22 |
20170175606 | Dosing Module - A dosing module for an emissions abatement system, the dosing module including an armature, means for moving the armature and a valve body having an outlet; the dosing module having an unblocked condition, in which the armature is moveable between a first position, in which the outlet is closed by the armature, and a second position, in which the armature is spaced apart from the outlet, and wherein, in use, application of electricity to the means for moving the armature at a first level of energy causes the armature to move from the first position to the second position; the dosing module further having a blocked condition, in which flow of a liquid through the outlet is prevented, wherein, in use, application of electricity to the means for moving the armature at a second level of energy causes the dosing module to change to the unblocked condition. | 2017-06-22 |
20170175607 | METHODS AND SYSTEMS FOR INTRODUCING REDUCTANT INTO AN EXHAUST PASSAGE - Methods and systems are provided for an exhaust passage having a plurality of catalysts. In one example, a method may include injecting reductant via one or more injectors of the exhaust passage and monitoring injection conditions by flowing exhaust gas to the engine. | 2017-06-22 |
20170175608 | SYSTEMS AND TECHNIQUES FOR NOZZLE COOLING OF DIESEL EXHAUST FLUID INJECTION SYSTEMS - A system is provided for delivery of diesel exhaust fluid or other reductant to an injector for release into an engine exhaust aftertreatment system. The injector includes a nozzle assembly that thermally shields the diesel exhaust fluid from the exhaust gas temperatures. A diesel exhaust fluid delivery procedure is also disclosed for nozzle cooling prior to operation of the injector for emissions reduction. | 2017-06-22 |
20170175609 | CATLYTIC CONVERTERS HAVING NON-LINEAR FLOW CHANNELS - Disclosed is a honeycomb catalyst substrate core having geometrically non-linear flow channels. In an embodiment, the honeycomb catalyst substrate core includes helical flow channels. In another embodiment, the honeycomb catalyst substrate core includes sinusoidal flow channels. In yet another embodiment, the honeycomb catalyst substrate core includes helical plus sinusoidal flow channels. The honeycomb catalyst substrate core comprises a plurality of parallel non-linear flow channels formed along a longitudinal axis of symmetry of the catalyst substrate core, each non-linear flow channel configured such that a turbulent vortical flow occurs during engine exhaust gas flow. Also disclosed is a method for manufacturing a ceramic honeycomb having non-linear flow channels, comprising the steps extrusion soft ceramic material through a die whilst the die moves through six degrees of freedom along its axis of symmetry. Disclosure includes a method for manufacturing a ceramic honeycomb having non-linear flow channels using three-dimensional printing. | 2017-06-22 |
20170175610 | EMISSIONS CONTROL NETWORK FOR HYBRID POWER PLANTS - A system, includes an emissions reduction system, including a catalyst system comprising an oxidation catalyst assembly and a selective catalytic reduction catalyst assembly. The system includes a diesel particulate fuel assembly, a first and a second sensor upstream of the catalyst system configured to measure emissions of the exhaust flow of the gas engine and a gas turbine before flowing into the catalyst system to generate a first and a second signal. A third sensor is downstream of the catalyst system to measure emissions of the catalyst system to generate a third signal, and a fourth and a fifth sensor disposed upstream and downstream of the DPF assembly to measure a change in pressure to generate a fourth signal and a controller to generate a first control signal to control an amount of reductant based on at least the first, second, and third signals. | 2017-06-22 |
20170175611 | COOLING STRUCTURE FOR MULTI-CYLINDER ENGINE - A cooling structure includes a block-side water jacket formed in a cylinder block, a head-side water jacket formed in a cylinder head, an introducing portion which introduces a cooling liquid from an end of the cylinder block to the block-side water jacket, a discharging portion which discharges a cooling liquid from the other end of the cylinder block to the head-side water jacket, and a spacer member accommodated in the block-side water jacket, and including a peripheral wall which forms an exhaust-side passage and an intake-side passage between a cylinder bore wall and the peripheral wall. The spacer member includes a distribution adjustment mechanism which distributes a cooling liquid introduced to the block-side water jacket between the exhaust-side passage and the intake-side passage. | 2017-06-22 |
20170175612 | VEHICULAR COOLING SYSTEM - An cooling system including an oil circulation circuit includes a first circuit including an electric oil pump that discharges oil as a coolant to be supplied to an inverter and respective motors, and an HV radiator that cools the oil to be supplied to the inverter and the respective motors, and a second circuit including a mechanical oil pump that discharges the oil to be supplied to a lubrication-required part without passing through the HV radiator. | 2017-06-22 |
20170175613 | THERMOSTAT STABILITY ENHANCEMENT VIA WAVY VALVE PLATE - A thermostat for use in the coolant passage of an internal combustion engine includes a valve seat and a valve plate with an elastomeric seal engaged with the valve seat in a closed condition and movable away from the valve seat in an open condition. The valve plate has a wavy surface disposed below the elastomeric seal that engages the valve seat, wherein the wavy surface is nonplanar with surface variations of at least 300 microns. The wavy valve plate creates a situation where the thermostat operates with two effective modes, a low flow regime for low load conditions where the valve is only traveling between 0 and approximately 1 mm while the wavy plate allows a low coolant flow and a high flow regime (valve fully open) for high engine load situations that require maximum cooling. | 2017-06-22 |
20170175614 | GASOLINE COMPRESSION IGNITION (GCI) ENGINE WITH DEDICATED-EGR CYLINDERS - The present disclosure provides a method comprising adjusting at least one of an air-to-fuel ratio and an ignition spark characteristic of a first cylinder of an engine to produce an exhaust gas comprising a predetermined quantity of hydrogen; and providing the exhaust gas from the first cylinder to a second cylinder of the engine, wherein the exhaust gas comprising the hydrogen ignites a first fuel type in response to a compression event. | 2017-06-22 |
20170175615 | Leading-Air Type Two-Stroke Air-Cooled Engine - To balance a “low-temperature scavenging effect” and a “high-temperature scavenging effect.” A scavenging system applicable to a leading-air type two-stroke air-cooled engine has a low-temperature scavenging passage and a high-temperature scavenging passage. The low-temperature scavenging passage has first and second passages and includes scavenging ports at upper end parts thereof. The high-temperature scavenging passage has first and second passages and includes scavenging ports at upper end parts thereof. An air is filled through a piston groove into the passages. The low-temperature scavenging passage has a relatively small capacity. The high-temperature scavenging passage has a relatively large capacity. | 2017-06-22 |
20170175616 | UNIFLOW SCAVENGING TWO-CYCLE ENGINE - A uniflow scavenging two-cycle engine includes an scavenging port having a swirling guide portion that guides scavenging gas into a cylinder in a direction inclined with respect to a radial direction of the cylinder, and a center guide portion that is provided to be closer to a crank side of the cylinder than the swirling guide portion and guides the scavenging gas further toward the center side of the cylinder than the swirling guide portion. At least a part of the center guide portion faces a piston when the piston is positioned at bottom dead center during the high compression ratio mode, and the center guide portion and the piston do not face each other or an area of facing the piston is smaller than that during the high compression ratio mode when the piston is positioned at bottom dead center during the low compression ratio mode. | 2017-06-22 |
20170175617 | CHARGE AIR COOLER SHROUD WITH ACCESS PANEL - A charge air cooler shroud is provided. That charge air cooler shroud includes a main body having an access opening and a removable access panel carried on the main body and covering the access opening. A method is also disclosed for mounting a cooling module to a frame of a motor vehicle. | 2017-06-22 |
20170175618 | TURBOCHARGER - A turbocharger includes a backflow passage that returns apart of gas flowing through a compressor wheel to a suction passage. The turbocharger includes an exhaust opening formed in a wall portion of an exhaust passage inside a compressor housing and that opens the exhaust passage to the outside of the compressor housing, a suction opening formed in a wall portion of the suction passage inside the compressor housing and that opens the suction passage to the outside of the compressor housing, and a backflow pipe of which one end is connected to the exhaust opening and the other end is connected to the suction opening and has the backflow passage inside thereof. In a state where the backflow pipe is removed from the exhaust opening and the suction opening, the suction opening is formed at a position at which the suction opening is visible when seen from a position opposite to the exhaust opening. | 2017-06-22 |
20170175619 | EXHAUST SOOT UTILIZED FOR EXTENDING THE LIFE OF A WASTEGATE - A number of variations may include providing a turbine housing including a wastegate valve including a shaft, a bushing, and a clearance disposed there between; the turbine housing furthering including a soot collector and a soot accelerator constructed and arranged to facilitate the flow of soot laden exhaust gas to the clearance. The method may further include collecting exhaust gas including soot via the soot collector; and providing soot within the clearance to lubricate the shaft and the bushing. | 2017-06-22 |
20170175620 | ROTARY ENGINE CASING - A rotary engine casing having at least one end wall of an internal cavity for a rotor including a seal-engaging plate sealingly engaging the peripheral wall to partially seal the internal cavity and a member mounted adjacent the seal-engaging plate outside of the internal cavity. The member and seal-engaging plate having abutting mating surfaces which cooperate to define between them at least one fluid cavity communicating with a source of liquid coolant. When the casing includes a plurality of rotor housings, the end wall may be between rotor housings. A method of manufacturing a rotary engine casing is also discussed. | 2017-06-22 |
20170175621 | ENGINE OPERABLE IN HORIZONTAL AND VERTICAL SHAFT ORIENTATIONS - A small air-cooled internal combustion engine includes an aluminum engine block including a cylinder, a crankcase reservoir, and an outer surface, a piston positioned within the cylinder and configured to reciprocate within the cylinder, and a crankshaft coupled to the piston and configured to rotate about a crankshaft axis, wherein a portion of the crankshaft is located in the crankcase reservoir, where the outer surface of the engine block has an edge located a radial distance from the crankshaft axis and the radial distance is less than less than a standard minimum distance between the crankshaft axis and a horizontal mounting surface for a standard garden mounting flange for a horizontally-shafted engine. | 2017-06-22 |
20170175622 | SLIDING ELEMENT - A sliding element, for example a piston ring for an internal combustion engine, may include a sliding face, an adhesive layer disposed on the sliding face, and a coating disposed over the adhesive layer. The coating may be composed of an amorphous carbon material. The coating may have a ratio between sp | 2017-06-22 |
20170175623 | Advanced Humid Air Gas Turbine System - One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine. When the gas turbine system is starting up, shut down or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator. | 2017-06-22 |
20170175624 | GAS TURBINE FACILITY - A gas turbine facility | 2017-06-22 |
20170175625 | SYSTEMS AND METHODS FOR AIR-BREATHING WAVE ENGINES FOR THRUST PRODUCTION - A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned. | 2017-06-22 |
20170175626 | GAS TURBINE ENGINE WITH MINIMIZED INLET DISTORTION - A gas turbine engine comprises a nacelle and a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle has inner periphery that is substantially axially symmetric about a center axis of the rotor from either a throat of the nacelle at a substantially bottom dead center location, or a point of inflection at which the inner periphery of the nacelle at substantially bottom dead center merges a convex portion into a concave portion. | 2017-06-22 |
20170175627 | AIR INTAKE TURBOPROP ASSEMBLIES - A turboprop assembly includes a nacelle with a main nacelle body and a nacelle extension coupled to the main nacelle body. The nacelle extension has a wall that defines an air intake port. The air intake port has a non-circular, non-rectangular, and non-oval shaped perimeter extending in two of three dimensions. | 2017-06-22 |
20170175628 | METHOD AND SYSTEM FOR INLET GUIDE VANE HEATING - A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures. | 2017-06-22 |
20170175629 | GAS TURBINE ENGINE WITH SHORT INLET AND ANTI-ICING FEATURES - A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. A distance is defined between an axial outer end of the nacelle, and a leading edge of the fan blade. An anti-icing treatment is provided to an inner periphery of the nacelle over at least 75% of the distance along the inner periphery of the nacelle. | 2017-06-22 |
20170175630 | HEAT EXCHANGE SYSTEM FOR A POWER GEAR BOX, A POWER GEAR BOX AND A TURBO ENGINE WITH A POWER GEAR BOX - A heat exchange system for a power gear box mechanically coupling at least low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box. | 2017-06-22 |
20170175631 | GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT ARRANGEMENT - A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil. | 2017-06-22 |
20170175632 | COOLING AIR HEAT EXCHANGER SCOOP - A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine. | 2017-06-22 |
20170175633 | TURBINE ENGINE CASE MOUNT AND DISMOUNT - A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine. | 2017-06-22 |
20170175634 | STAGED FUEL AND AIR INJECTION IN COMBUSTION SYSTEMS OF GAS TURBINES - A gas turbine that includes a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section that corresponds to the aftward annulus section and a forward intake section that corresponds to the forward annulus section. The air directing structure may be configured to: direct air entering through the aftward intake section through the aftward annulus section in a forward direction to the staged injector; and direct air entering through the forward intake section through the forward annulus section in an aftward direction to the staged injector. | 2017-06-22 |
20170175635 | STAGED FUEL AND AIR INJECTION IN COMBUSTION SYSTEMS OF GAS TURBINES - A gas turbine that includes a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section that corresponds to the aftward annulus section and a forward intake section that corresponds to the forward annulus section. The air directing structure may be configured to: direct air entering through the aftward intake section through the aftward annulus section in a forward direction to the staged injector; and direct air entering through the forward intake section through the forward annulus section in a forward direction to the forward injector. | 2017-06-22 |
20170175636 | STAGED FUEL AND AIR INJECTION IN COMBUSTION SYSTEMS OF GAS TURBINES - A gas turbine including a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus, and a third radial wall formed about the outer radial wall that forms an outer flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section corresponding to the aftward annulus section and a forward intake section corresponding to the forward annulus section. The air directing structure may include a switchback coolant flowpath to direct air from the compressor discharge cavity to the staged injector. The switchback coolant flowpath may include an upstream section through the flow annulus, and a downstream section through the outer flow annulus. | 2017-06-22 |
20170175637 | STAGED FUEL AND AIR INJECTION IN COMBUSTION SYSTEMS OF GAS TURBINES - A gas turbine that includes: a combustor coupled to a turbine that together define a working fluid flowpath; a compressor discharge cavity; a staged injector; stator blade airfoils extending between inboard and outboard sidewalls; and a first and second coolant flowpath. The first coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the inboard sidewall; an outtake section including a downstream port connected to the staged injector and an upstream port formed through the outboard sidewall; and a cooling circuit through the airfoil. The second coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the outboard sidewall; an outtake section that comprises a downstream port connected to the staged injector and an upstream port formed through the inboard sidewall; and a cooling circuit through the airfoil. | 2017-06-22 |
20170175638 | FALSE START DRAIN SYSTEM WITH VERTICAL HEADER - A drain system for a combustor of a gas turbine includes a plurality of drain tubes, a vertical header connected to an end of each drain tube to receive a fluid flow therefrom, and a horizontal header downstream of the vertical header and in fluid communication therewith. Each drain tube has another end adapted to be connected to a respective combustor can of the gas turbine to drain liquid therefrom. The vertical header is disposed at an angle between 30° and 90° with a horizontal plane. | 2017-06-22 |
20170175639 | ENGINE FUEL SYSTEM FOR USE WITH COMPOSITE AIRCRAFT - A fuel system for a composite aircraft is described which includes an ejector pump having a vacuum inlet in communication with a fuel storage tank, an engine feed pump having an inlet in fluid communication with an outlet of the ejector pump, a primary outlet in communication with an engine, and a motive flow outlet, upstream of an oil-fuel heat exchanger, that is in fluid communication with an inlet of the ejector pump. A motive flow pump assembly is disposed between the motive flow outlet of the engine feed pump and the inlet of the ejector pump. The motive flow pump assembly includes an inlet screen and a motive flow pump, the inlet screen having a plurality of openings therein and a hydrophobic upstream surface. The openings are dimensioned to prevent passage of particles greater than a selected threshold size while allowing liquids to flow therethrough. | 2017-06-22 |
20170175640 | HIGH PRESSURE EXHAUST MUFFLING DEVICE WITH MULTIPLE SOURCES - A muffling device for exhausting at least one fluid flow in a gas turbine engine includes a first diffuser coupled in flow communication with a first conduit. The first diffuser is configured to exhaust a first fluid flow. The device further includes a second diffuser disposed adjacent the first diffuser. The second diffuser is coupled in flow communication with a second conduit. The second diffuser is configured to exhaust a second fluid flow. The device also includes a third diffuser at least partially surrounding the first diffuser and the second diffuser. The third diffuser is coupled in flow communication with the first diffuser and the second diffuser. The third diffuser includes a body with apertures and is configured to exhaust a third fluid flow. The third fluid flow includes at least one of the first fluid flow and the second fluid flow. | 2017-06-22 |
20170175641 | GAS TURBINE COMBUSTION ACOUSTIC DAMPING SYSTEM - A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing. | 2017-06-22 |
20170175642 | METHODS AND APPARATUS FOR NOISE ATTENUATION IN AN ENGINE NACELLE - An inner barrel for a nacelle for an engine is provided. The inner barrel includes a radially inner acoustic liner and a radially outer structural barrel. The structural barrel includes a flange for coupling the inner barrel to the nacelle. At least a portion of the flange is formed integrally with the structural barrel. | 2017-06-22 |
20170175643 | SYSTEM FOR THE EMERGENCY STARTING OF A TUROMACHINE - The invention relates to a system for emergency starting a turbine engine, characterised in that it comprises a flyer for driving the turbine engine, said flyer comprising a drum ( | 2017-06-22 |
20170175644 | MACHINE-SPECIFIC PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR POWER OUTPUT-EMISSIONS PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - A system includes: a computing device configured to tune a set of gas turbines (GTs) by: commanding each GT to a base load level; commanding each GT to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; updating a pre-existing emissions model for each GT based upon the adjusted operating condition; running a set of operating conditions on each GT and measuring an updated emissions value; and refining the updated pre-existing emissions model based upon a difference between the updated emissions value and the updated pre-existing emissions model. | 2017-06-22 |
20170175645 | ENHANCED PERFORMANCE OF A GAS TURBINE - In one embodiment, a system may include a gas turbine system. the gas turbine system includes a gas turbine, an after-treatment system that may receive exhaust gases from the gas turbine system, and a controller that may receive inputs and model operational behavior of an industrial plant based on the inputs. The industrial plant may include the gas turbine and the after-treatment system. The controller may also determine one or more operational parameter setpoints for the industrial plant, select the one or more operational parameter setpoints that reduce an output of a cost function, and apply the one or more operational parameter setpoints to control the industrial plant. | 2017-06-22 |
20170175646 | METHOD AND SYSTEM FOR STALL MARGIN MODULATION AS A FUNCTION OF ENGINE HEALTH - A stall margin modulation (SMM) control system in communication with a gas turbine engine including a compressor is described herein. The SMM control system is configured to determine the stall margin of the compressor, operate the gas turbine engine using the determined stall margin, assess a health of the compressor, and modify the stall margin based on the assessed health of the compressor. | 2017-06-22 |
20170175647 | COMBINED PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR POWER OUTPUT-EMISSIONS PARAMETERS WITH SCALING FACTOR, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - Commanding GTs to base load level based upon measured ambient condition for each GT; commanding each GT to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and an emissions scale factor, wherein the nominal emissions value at the ambient condition and the emissions scale factor are stored in a pre-existing emissions model for the GT. | 2017-06-22 |
20170175648 | PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR POWER OUTPUT-EMISSIONS PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and setting a target operating condition for each GT to match the adjusted operating condition after the adjusting of the operating condition. | 2017-06-22 |
20170175649 | APPLICATION OF COMBINED PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR POWER OUTPUT-EMISSIONS PARAMETERS WITH SCALING FACTOR, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: modelling each GT in the set of GTs at a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition. | 2017-06-22 |
20170175650 | APPLICATION OF COMBINED PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR POWER OUTPUT-EMISSIONS PARAMETERS WITH SCALING FACTOR, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and modeling an emissions value for the GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective modelled emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition. | 2017-06-22 |
20170175651 | MODELLING PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR POWER OUTPUT-EMISSIONS PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and building an independent emissions model for each GT based upon the measured actual emissions value for each GT and the adjusted operating condition of each GT. | 2017-06-22 |
20170175652 | METHOD FOR CHECKING THE FUNCTION OF A COMPRESSION RELEASE BRAKE SYSTEM - Function of a compression release brake system of a compression ignited engine with a plurality of cylinders in a motor vehicle is checked by driving a crank shaft of the engine to rotate at a constant speed without injection of fuel into the cylinders while for each cylinder, for the compression release brake system in an inactive state and then in an active state, measuring the torque to be applied for maintaining said speed in a position of said crank shaft where the torque would be influenced by the behavior of that cylinder by a correctly functioning action of said compression release brake system in an active state. The torque values obtained for each cylinder for the compression release brake system in inactive and active state are compared, and the function of the compression release brake system for each individual cylinder of the engine is determined based on the comparison. | 2017-06-22 |
20170175653 | FUEL INJECTION CONTROLLER FOR INTERNAL COMBUSTION ENGINE - A fuel injection controller for an internal combustion engine is provided. The fuel injection controller includes an electronic control unit configured to (a) execute main fuel injection and auxiliary fuel injection in one engine cycle; and (b) execute the auxiliary fuel injection at least once in a particular period that includes timing at which a intake valve starts opening, so that fuel injected in the auxiliary fuel injection is carried by a reverse tumble stream, the reverse tumble stream being an air stream that flows from a intake port into a combustion chamber, flows along a bore wall surface on the intake valve side that is on an opposite side from a exhaust valve toward a piston crown surface, and then flows from the piston crown surface toward a cylinder head lower surface. | 2017-06-22 |
20170175654 | ENGINE SYNCHRONIZATION APPARATUS AND CONTROL METHOD THEREOF - An engine synchronization apparatus includes: a crank shaft position sensor detecting a position of a crank shaft to detect a tooth and a missing tooth; a cam sensor detecting a position of a cam corresponding to an angle of rotation of each of an intake cam and an exhaust cam; and a controller synchronizing the engine to use a tooth detection signal from the crank shaft position sensor and a cam signal from the cam sensor. The controller carries out an engine synchronization by determining the position of the crank shaft and the position of the cam to select one cam between the intake cam and the exhaust cam and to detect the position of a unique part of the cam signal from a voltage level and a level length of the cam signal of the selected cam. | 2017-06-22 |
20170175655 | METHOD FOR OPERATING AN ENGINE - A method for operating an engine includes selectively introducing air in an exhaust conduit upstream of a selective catalytic reduction system based on an exhaust gas temperature and a nitrous oxide conversion efficiency of the selective catalytic reduction system and changing at least one engine operating map for engine operation when the nitrous oxide conversion efficiency after introducing air is above a threshold nitrous oxide conversion efficiency. | 2017-06-22 |
20170175656 | CONTROL SYSTEM FOR AN INTERNAL COMBUSTION ENGINE - In a control system for an internal combustion engine in which an exhaust gas purification catalyst having a lower catalyst layer and an upper catalyst layer disposed at the upper side of the lower catalyst layer is arranged in an exhaust passage of the internal combustion engine, when an operation at a rich air fuel ratio is switched to an operation at a target lean air fuel ratio, switching is made through a first operation in which the air fuel ratio of exhaust gas is temporarily made into a lean air fuel ratio, and a second operation which is carried out after the first operation and in which the air fuel ratio of the exhaust gas is made to change alternately between the rich air fuel ratio and the lean air fuel ratio a plurality of times, whereby the HC poisoning of the catalyst can be recovered at an early stage. | 2017-06-22 |