52nd week of 2018 patent applcation highlights part 37 |
Patent application number | Title | Published |
20180371913 | Rotor and Vane with Insert - A rotor assembly has a vane which engages an eccentric cam block using an insert. The insert is removably attached to the vane. The vane is captured within a transverse slot in the rotor and executes reciprocal motion transversely to the axis of rotation of the rotor as the rotor rotates. | 2018-12-27 |
20180371914 | SYSTEMS AND METHODS FOR RECONTOURING ENGINE COMPONENTS - Systems and methods that include and/or leverage a cluster of machine-learned models to recontour components of gas turbine engines are provided. In one exemplary aspect, the systems and methods leverage a cluster of machine-learned models to predict repair machining offsets for certain sections of the component that can be used to adjust or set a material removal tool path. | 2018-12-27 |
20180371915 | DEVICES AND METHODS FOR BALANCING A HIGH-PRESSURE SPOOL OF A GAS TURBINE ENGINE - Devices and methods useful for balancing high-pressure spools of gas turbine engines are disclosed. An exemplary device may comprise: an input shaft configured to be coupled to an output of an accessory gear box driven by a high-pressure spool of a gas turbine engine; a first trigger rotatably coupled to the input shaft at a first speed ratio; and a sensor configured to detect the trigger at each revolution of the trigger. The first speed ratio may permit a rotational speed of the first trigger to be substantially the same as a rotational speed of the high-pressure spool. Upon detection of the trigger, the sensor may generate one or more signals representative of each associated revolution of the high-pressure spool of the gas turbine engine. | 2018-12-27 |
20180371916 | ROTOR FOR A TURBOMACHINE - A rotor for a turbomachine, includes a plurality of axially adjacently arranged rotor segments which are each provided with a central opening, an individual tie rod extending through the openings of the rotor segments, and two holding devices which are arranged on axially opposing ends of the tie rod and hold the rotor segments together, the rotor segments forming at least two rotor segment groups between which at least one other holding device is arranged. | 2018-12-27 |
20180371917 | STEAM TURBINE - A steam turbine is for a combined cycle plant. The combined cycle plant includes a gas turbine; a boiler a heat source of which is a flue gas discharged from the gas turbine; a high-pressure steam turbine that includes a rotor extending along an axial center of rotation of the rotor, a steam passage provided along the extending direction of the rotor between the rotor and a casing for the rotor, and a high-pressure steam supply portion provided to communicate, from outside the casing through the casing, with the steam passage and configured to be supplied with superheated steam, the high-pressure steam turbine being driven by high-pressure steam generated by the boiler; and a low-pressure steam turbine configured to be driven by low-pressure steam generated by the boiler and by the steam that has flowed through the high-pressure steam turbine. | 2018-12-27 |
20180371918 | TURBOMACHINE AND TURBINE BLADE THEREFOR - A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with a fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. A trailing edge of the airfoil deviates from an axial plane and a circumferential plane. A corresponding turbomachine comprising a plurality of such blades is also provided. | 2018-12-27 |
20180371919 | SECONDARY FLOW CONTROL - A slot is provided in an endwall of a flow passage, for example between two stator vanes or rotor blades of a gas turbine engine. The length direction of the flow passage is aligned substantially with the main flow through the flow passage. The alignment of the slot means that the “over-turned” boundary layer flow can be extracted through the slot but with minimal impact on the mainstream flow. | 2018-12-27 |
20180371920 | ADDITIVELY MANUFACTURED HOLLOW BODY COMPONENT WITH INTERIOR CURVED SUPPORTS - A hollowed body component made by additive manufacturing is disclosed. The hollow body has a longitudinal extent, an exterior surface and an interior surface, the interior surface having a first side and an opposing, second side. A first set of curved supports are curved along lengths thereof and extend between the first side and the opposing, second side to support the hollow body at least during the additive manufacturing thereof. Some embodiments include cooling passages open to the interior surface. Here, the curved supports extend between opposing pairs of passage-free spaces on the interior surface to support the hollow body at least during the additive manufacturing thereof. In one example, the component is an impingement insert for a hot gas path component. | 2018-12-27 |
20180371921 | TURBOMACHINE ROTOR BLADE - The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud includes a side surface. The airfoil and the tip shroud define a first cooling passage. The tip shroud further defines a second passage in fluid communication with the first cooling passage. The second cooling passage extends from the first cooling passage to a first outlet defined by the side surface. The first outlet is configured to direct a flow of coolant onto a tip shroud fillet of a first adjacent rotor blade. | 2018-12-27 |
20180371922 | COMPOSITE TURBOMACHINE COMPONENT AND RELATED METHODS OF MANUFACTURE AND REPAIR - Various aspects include a composite turbomachine component and related methods. In some cases, a method includes: identifying a location of potential or actual structural weakness in a body of a turbomachine component, the body including a first material having a first thermal expansion coefficient; forming a slot in the location of the body, the slot extending at least partially through a wall of the turbomachine component; and bonding an insert to the body at the slot to form a composite component, the insert including a second material having a second thermal expansion coefficient differing from the first thermal expansion coefficient by up to approximately ten percent, the second material consisting of a nickel-chromium-molybdenum alloy, wherein after the bonding the insert is configured to reduce the potential or actual structural weakness in the body. | 2018-12-27 |
20180371923 | SLOTTED CERAMIC COATINGS FOR IMPROVED CMAS RESISTANCE AND METHODS OF FORMING THE SAME - Methods for preparing slotted ceramic coatings and the resulting components comprising the same are provided. The methods and products include the incorporation of a coating system comprising a ceramic coating with cooling holes disposed throughout the ceramic coating and slots defined in the thermal barrier coating and disposed in relation to the cooling holes. The resulting ceramic coating has improved resistance to CMAS infiltration and improved compliance resulting in an increased life of the coated component. | 2018-12-27 |
20180371924 | Additively Manufactured Blisk with Optimized Microstructure for Small Turbine Engines - An integrally bladed rotor in which a hub and a web are formed from a fine grain microstructure using an investment casting process or from metal powder with a HIP process, and a plurality of rotor blades formed from a coarse grain microstructure using a metal additive manufacturing process, where the hub and the web and the rotor blades are formed as a single piece and from the same material. | 2018-12-27 |
20180371925 | TURBINE VANE COMPRISING A BLADE WITH A TUB INCLUDING A CURVED PRESSURE SIDE IN A BLADE APEX REGION - A turbine vane of a turbine engine such as a turbojet. The vane includes a base supporting a blade that extends in a spanwise direction and ends in an apex. The blade includes a pressure-side wall and a suction-side wall, each ending at an end edge at the apex of the blade. The blade includes, at the apex thereof, a closed wall extending from the pressure-side wall to the suction-side wall so as to define, with the end edges, a tub shape. The pressure-side wall is curved inward so as to deviate from the spanwise direction in the region of the blade apex preceding the tub, between the base and the pressure-side end edge. | 2018-12-27 |
20180371926 | SLIDING BAFFLE INSERTS - A vane includes a vane body extending from a root to an opposed tip along a longitudinal axis and first and second baffle bodies. The vane body defines a leading edge and a trailing edge, and a cavity defined between the leading edge, the trailing edge, the root and the tip. The vane body includes at least one vane rib defined between the leading edge and the trailing edge inside the cavity. The first baffle body is defined in one of a leading edge portion and a trailing edge portion of the cavity. The second baffle body is defined in a middle portion of the cavity. | 2018-12-27 |
20180371927 | SEAL STRUCTURE AND TURBINE - A seal structure is for sealing leakage fluid flowing through a gap between a rotation member rotating about a rotation axis and a stationary member facing the rotation member. The seal structure includes seal fins projecting from a base that is one of the rotation and stationary members toward the other one, the seal fins being spaced apart from each other at a certain interval in an axial direction of the rotation axis; and a step section provided to the other one, the step section including step surfaces facing the seal fins and a riser surface between the adjacent step surfaces, the step surfaces and the riser surface defining a step portion. The seal fins are inclined upstream in a flow direction of the leakage fluid relative to a radial direction perpendicular to the rotation axis. Each seal fin and the base define a corner portion having a curved surface. | 2018-12-27 |
20180371928 | BRUSH SEAL - Provided is a brush seal in which the leakage of a sealed fluid is small. The brush seal includes: a brush formed of a bunch of a plurality of bristles; and an annular back plate arranged at a low-pressure side of the brush and provided with a plurality of grooves into which a sealed fluid is to be introduced. In the brush seal, the plurality of grooves are inclined with respect to a circumferential direction of the back plate and with respect to an extending direction (B) of the brush. | 2018-12-27 |
20180371929 | BEARING ASSEMBLY FOR GAS TURBINE ENGINES - A bearing assembly according to an example of the present disclosure includes, among other things, a bearing situated in a bearing compartment, a seal assembly that defines the bearing compartment, at least one deflector between the bearing and the seal assembly that is rotatable about an axis, and a coalescer at least partially extending about the at least one deflector to define a fluid passage. A method of sealing is also disclosed. | 2018-12-27 |
20180371930 | CERAMIC MATRIX FULL HOOP BLADE TRACK - A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints. | 2018-12-27 |
20180371931 | TURBINE SHROUD SEGMENT WITH BUFFER AIR SEAL 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 air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine. | 2018-12-27 |
20180371932 | ABRADABLE COATING HAVING VARIABLE DENSITIES - A method of fabricating an abradable coating of varying density, and an abradable coating of varying density. The method comprises the following steps: providing a substrate having a first portion and a second portion; depositing a first precursor material on the first portion of the substrate compressing the first precursor material between the substrate and a first bearing surface; sintering the first precursor material as compressed in this way in order to obtain a first abradable coating portion on the first portion of the substrate, and possessing a first density; depositing a second precursor material on the second portion of the substrate; and compressing the second precursor material between the substrate and a second bearing surface. | 2018-12-27 |
20180371933 | OPTIMIZED ENGINE CONTROL WITH ELECTRIFIED INTAKE AND EXHAUST - In one aspect, the teachings presented herein include a power generation system including: a power plant having an air intake and an exhaust outlet; a boost device in fluid communication with the power plant air intake, the boost device being for pressurizing air entering the power plant air intake; a waste heat recovery device in fluid communication with the power plant exhaust outlet, the waste heat recovery device being for recovering energy from exhaust from the power plant; a first motor/generator coupled to the boost device; a second motor/generator coupled to the waste heat recovery device; an energy storage device for storing energy generated by the first and second motor/generators and for delivering power to drive the first motor/generator; a controller for controlling the first and second motor/generators, wherein the controller is configured to control the level of power generated by the waste heat recovery device based on a state of charge of the energy storage device. | 2018-12-27 |
20180371934 | SCREW EXPANDER - A screw expander includes a main body, at least an expansion screw and an adjusting component. The main body has a high pressure region, an expansion region and a low pressure region. The expansion screw is disposed at the expansion region and has an air inlet end and an air outlet end, wherein the air inlet end is connected to the high pressure region, and the air outlet end is connected to the low pressure region. The adjusting component covers the expansion screw, and is adapted to move relatively to the expansion screw to change an opening area of the air inlet end or an opening area of the air outlet end, such that a pressure of an air exhausted from the air outlet end is adjusted. | 2018-12-27 |
20180371935 | VALVE SYSTEM AND STEAM TURBINE - A valve system includes: a valve device with a flow path and a valve body that opens and closes the flow path; and a drive mechanism that drives the valve body. The drive mechanism includes: a cylinder case; a cylinder chamber that extends in an axis direction and is formed inside the cylinder case; a piston that divides the cylinder chamber into a first chamber on a first side in the axis direction and a second chamber on a second side in the axis direction; an inflow port through which working fluid flows to the inside of the first chamber; an elastic member disposed inside the second chamber and that pushes the piston to the first side; a bypass passage that connects the first chamber and the second chamber; and an on-off valve that opens and closes the bypass passage. | 2018-12-27 |
20180371936 | METHOD AND SYSTEM FOR SCHEDULE PREDICTIVE LEAD COMPENSATION - A method and system of scheduling a demand for a process inner loop are provided. The loop controller includes an inner loop control system configured to generate a control output signal for a controllable member and a schedule demand module configured to receive parameter values for a controlled variable of a process from a parameter source and to generate a scheduled demand output using a demand schedule. The loop controller also includes a schedule prediction module configured to predict a future value of a scheduling parameter based on a historical performance of the inner loop control system and current system dynamics and to generate a scheduled rate output. The schedule prediction module includes the rate-of-change of a scheduling parameter and a lead time input that defines a look-ahead time period used with the parameter rate signal to determine a future predicted value of the controlled variable. | 2018-12-27 |
20180371937 | SPLIT SYNCHRONIZATION RING FOR VARIABLE VANE ASSEMBLY - A synchronization ring for a variable vane assembly of a gas turbine engine may include a first ring portion and a second ring portion. The first ring portion and the second ring portion may be detachably coupled together to jointly define a plurality of cylindrical bores circumferentially distributed around the synchronization ring and extending radially through the synchronization ring. | 2018-12-27 |
20180371938 | Method and Configuration for Improved Variable Vane Positioning - According to one aspect, an apparatus for controlling a vane comprises an actuator, a vane control rod, a guide pin disposed on the vane control rod, a sleeve disposed about the vane control rod, and at least one sleeve track disposed along an extent of the sleeve. Further in accordance with this aspect, the guide pin couples the vane control rod and the sleeve, and the actuator linearly moves the vane control rod through the sleeve in order to manipulate a position of the vane. | 2018-12-27 |
20180371939 | VARIABLE-PITCH BLADE CONTROL RING FOR A TURBOMACHINE - Variable-pitch blade control ring ( | 2018-12-27 |
20180371940 | SYSTEMS AND METHODS RELATED TO TRANSMITTING AND RECEIVING SENSOR DATA - A system for transmitting discrete data packets of sensor measured values of operating parameters. The system includes a transmitting device configured to transmit the measured values per a transmittal protocol. The system includes a receiving device that receives the measured values processes the received measured values in accordance with a receiving protocol. The transmittal protocol includes: determining a most recent measured value for the sensor; selecting previous measured values for the sensor; comparing the most recent measured value to the previous measured values to determine a difference therebetween; and conditionally transmitting the most recent measured value based on the difference. The receiving protocol includes: determining a most recent received measured value for each of the sensors; deriving an analytic time based the most recent received measured values; and deriving a time-aligned value for one of the operating parameters measured by the sensors at the analytic time. | 2018-12-27 |
20180371941 | GASPATH COMPONENT INCLUDING MINICORE PLENUMS - A turbine engine component includes a wall extending from a leading edge to a trailing edge. The wall includes a hot side facing a gaspath when the gaspath component is in an installed state, and a cold side opposite the hot side. At least one minicore cooling circuit is disposed between the hot side and the cold side within the wall. At least one cooling fluid inlet connects the minicore cooling circuit to a coolant source. At least one film cooling hole connects the minicore cooling circuit to the hot side surface. The minicore cooling circuit includes an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the minicore cooling circuit normal to the hot side surface. The edge plenum is a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge. | 2018-12-27 |
20180371942 | ELLIPTICAL SLOT WITH SHIELDING HOLES - A turbine shaft comprising: a tubular body having an outer surface and an inner surface opposite the outer surface, the inner surface defining a hollow chamber within the tubular body, wherein the tubular body includes a first longitudinal axis concentric to the tubular body; and one or more shielded elliptical orifices, at least one shielded elliptical orifice comprising: an elliptical orifice in the tubular body including a major axis extending from a first side to a second side of the elliptical orifice, wherein the major axis is oriented at an angle parallel with a torque field of the tubular body; a first shielding orifice in the tubular body having a first axis collinear to the major axis; and a second shielding orifice in the tubular body having a second axis collinear to the major axis, wherein the elliptical orifice is located in between the first and second shielding orifice. | 2018-12-27 |
20180371943 | COOLING FEATURES FOR A GAS TURBINE ENGINE TRANSITION DUCT - A gas engine turbine has a transition duct ( | 2018-12-27 |
20180371944 | OIL JET FOR TURBINE ENGINE - An oil jet for a turbine engine, comprising a body including a circulation pipe intended for the flow of a pressurized fluid. The jet's body comprises a first part and a second part between which a resiliently deformable membrane is inserted, said membrane being capable of deforming between a sealed position in which it prevents the circulation of the fluid in the pipe and a position in which it allows the circulation of fluid in the pipe. The second part includes bearing means configured to exert a force on the membrane positioned in the opposite direction to the circulation of fluid so as to preload the membrane when in blocked position. | 2018-12-27 |
20180371945 | SYSTEM AND METHOD FOR SUPPLYING LUBRICATION FLUID TO AT LEAST ONE MEMBER OF AN AIRCRAFT PROPULSION ASSEMBLY - A feed system for feeding lubricating oil to members of a turbine engine including a reduction gearbox, the feed system including a nonpositive-displacement pump device for connecting upstream to an oil tank and driven in rotation at a speed that is not correlated with an operating speed of the turbine engine; a separator node connected to the outlet of the nonpositive-displacement pump device; a first delivery branch for lubricating the RGB connected to the nonpositive-displacement pump device via the separator node; a second delivery branch for lubricating other members connected to the nonpositive-displacement pump device via the separator node, the second delivery branch including a positive-displacement pump; and at least one fluid metering device having a metering slot fed by the nonpositive-displacement pump device via the separator node for the purpose of feeding the RGB. | 2018-12-27 |
20180371946 | GAS TURBINE DUCT LINER COUPLING ASSEMBLY - A duct liner assembly for a gas turbine engine includes a first ring and a second ring. Also included is a first duct liner having a first end and a second end, the first duct liner mounted proximate the first end of the first duct liner to the first ring. Further included is a second duct liner having a first end and a second end, the second duct liner mounted proximate the second end of the second duct liner to the second ring. Yet further included is a coupling assembly including a threaded insert, a retaining bracket, and a threaded fastener extending through the retaining bracket and in threaded engagement with the threaded insert to couple the retaining bracket to the second duct liner. | 2018-12-27 |
20180371947 | CERAMIC MATRIX COMPOSITE JOINTS - An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together. | 2018-12-27 |
20180371948 | ASSEMBLY FOR A SPREADER CONNECTION BETWEEN A TURBINE CASING AND A TURBINE ENGINE RING ELEMENT - An assembly comprising ring sectors made of a first material, the sectors being placed circumferentially end to end and suspended from an outer casing, and radial positioning means comprising at least one annular tongue made of a different material, for fastening the ring sectors to the outer casing, by an annular support. The radial positioning means further comprise an eccentric spreader engaged on one side with said at least one annular tongue and, on the other side, with the sectorized annular element, and acting to enable the distance between the annular tongue and the sectorized annular element to be adjusted radially. | 2018-12-27 |
20180371949 | PLANT SYSTEMS - Plant systems are disclosed A disclosed example plant system includes a first assembly carried by a machine frame, and a second assembly coupled to an interface of the first assembly, where the interface has an interface axis along which at least one of a force flux, a torque flux, or a media flux can take pass from the first assembly and into the second assembly via the interface. The machine frame carries the second assembly. | 2018-12-27 |
20180371950 | METHODS AND DEVICES FOR TURBINE BLADE INSTALLATION ALIGNMENT - Devices, systems and methods of the present disclosure can include a guide for installing an airfoil component in a slotted component of a gas turbine engine. The guide can comprise a guide body, a guide slot and an alignment appendage. The guide body can comprise a slot-facing side, an entry side, and a radially outer side surface connecting the slot-facing side and the entry side. The guide slot can extend from the entry side to the slot-facing side and can penetrate the radially outer side surface. The guide slot can have a silhouette matching that of a root portion of the airfoil component. The alignment appendage can extend from the guide body and can have a geometry for axial engagement with a circumferential feature of the slotted component into which the airfoil component is to be installed. | 2018-12-27 |
20180371951 | PROTECTIVE BAFFLES FOR GAS TURBINE NOISE ATTENUATION SYSTEM - The present application provides an exhaust system to exhaust combustion gases from a gas turbine engine. The exhaust system may include an exhaust collector and an exhaust stack with a silencer section. The silencer section may include a number of baffles therein. The baffles may include a number of nose cones facing the combustion gases. The nose cones may include a first shape and a second shape. | 2018-12-27 |
20180371952 | BACKFLOW PREVENTION SYSTEM FOR A GAS TURBINE ENGINE - The present application provides an exhaust system to exhaust a flow of combustion gases and a flow of ventilation air from a gas turbine engine. The exhaust system may include an exhaust collector, a transition duct downstream of the exhaust collector, the exhaust collector positioned within an engine room, and a backflow prevention system positioned about the exhaust collector, the engine room, and the exhaust collector so as to prevent a backflow of the combustion gases into the engine room. | 2018-12-27 |
20180371953 | DRY COOLING SYSTEM USING THERMALLY INDUCED VAPOR POLYMERIZATION - A system and method for providing dry cooling of a coolant in a directed energy system, having a plurality of heat exchangers which depolymerize and polymerize a polymer. Specifically, the depolymerization process is endothermic and draws heat from a source liquid in a first heat exchanger, and the polymerization process is exothermic and expels heat from a second heat exchanger. Additional heat exchangers and holding tanks may be incorporated in the system and method. Pumps having adjustable volumetric flow may be incorporated and provide customized cooling and energy draw. | 2018-12-27 |
20180371954 | INVERTED BRAYTON CYCLE HEAT ENGINE - An apparatus ( | 2018-12-27 |
20180371955 | COGENERATION SYSTEM - A cogeneration system ( | 2018-12-27 |
20180371956 | STACK ENERGY CONTROL IN COMBINED CYCLE POWER PLANT - A combined cycle power plant and method for operating a combined power plant with stack energy control are presented. The combined cycle power plant includes a gas turbine, a heat recovery steam generator including a plurality of heating surfaces, and a steam turbine. The heating surfaces may be partially bypassed to reduce steam production in the heat recovery steam generator during power plant startup. Less energy may be extracted from exhaust gas of the gas turbine. More energy may be dumped through an exhaust stack. The steam turbine may start without restriction of a gas turbine load during power plant startup. The steam turbine may start without increasing a size of an air cooled condenser while maintaining a higher load of a gas turbine during power plant startup. | 2018-12-27 |
20180371957 | THERMODYNAMIC CYCLE SYSTEM - A thermodynamic cycle such as an organic Rankine cycle system, utilizing a lubricant and a working fluid, for a machine in which pressurized gaseous working fluid is expanded to a lower pressure level and the energy from the fluid expansion is transformed into mechanical rotation energy; the lubricant includes a polyalkylene glycol based lubricant composition and the working fluid includes a mixture of alcohol and water. | 2018-12-27 |
20180371958 | HEAT CYCLE SYSTEM AND HEAT CYCLE METHOD USING THE SAME - There are provided a heat cycle system that uses a system for heat cycle designed to use 1,1,1,3,3-pentafluoropropane (HFC-245fa) as a working fluid as it is and is thereby excellent in economic efficiency, and is equal to or higher in cycle performance and lower in environmental burden than in the case of using HFC-245fa, and a heat cycle method using the heat cycle system. The heat cycle system includes a working fluid and a system for heat cycle, the system for heat cycle is suitable for HFC-245fa being used as a working fluid, and the working fluid contains 1-chloro-2,3,3,3-tetrafluoropropene, and the heat cycle method uses the heat cycle system. | 2018-12-27 |
20180371959 | Balanced-Pressure Multi-Compartment Vessel, Thermodynamic Energy Converter and Operating Method - The invention relates to a thermodynamic energy converter ( | 2018-12-27 |
20180371960 | CAMSHAFT AND MANUFACTURING METHOD THEREFOR - Multiple tubular members | 2018-12-27 |
20180371961 | FORCE TRANSMISSION DEVICE - The present disclosure relates to a force transmission device for connection between a cam-shaft and a gas exchange valve including a main body with a receptacle which extends along a longitudinal axis. The force transmission device has an actuating piston which is provided in the receptacle such that it can move between a first position and a second position, and a contact body for actuating the gas exchange valve and in operative connection with the actuating piston. The force transmission device has a first blocking piston which is provided in the receptacle such that it can move in a radial direction with respect to the longitudinal axis between a third position, in which the first blocking piston blocks the actuating piston in the first position, and a fourth position, in which the first blocking piston releases a movement of the actuating piston between the first position and the second position. | 2018-12-27 |
20180371962 | VARIABLE CAM PHASER WITH DAMPER - A variable cam phaser system including a variable cam phaser and a vibration damper fixed to the variable cam phaser is disclosed. A method for damping vibration for a variable cam phaser is also disclosed. The method includes providing a variable cam phaser, providing a vibration damper, and fixing the vibration damper to the variable cam phaser. | 2018-12-27 |
20180371963 | CAM PHASING ASSEMBLIES WITH ELECTROMECHANICAL LOCKING CONTROL AND METHOD THEREOF - A cam phasing control motor assembly, including: an electric motor with a hollow drive shaft; an actuating pin passing through the hollow drive shaft; an engagement feature; and a displacement assembly. For a camshaft locking mode: the displacement assembly displaces the actuating pin in a first axial direction to non-rotatably connect the engagement feature with a bolt non-rotatably connected to a camshaft; and the camshaft is arranged to non-rotatably connect to an input gear for a gearbox phasing unit, the input gear arranged to receive torque from an engine. For a phase adjusting mode: the displacement assembly displaces the actuating pin in a second axial direction, opposite the first axial direction, to disconnect the engagement feature from the bolt; and the camshaft is arranged to rotate with respect to the input gear. | 2018-12-27 |
20180371964 | VALVE OPENING AND CLOSING TIMING CONTROL APPARATUS - A valve opening and closing timing control apparatus includes a driving-side rotation member, a driven-side rotation member, a phase adjustment mechanism configured as a differential type reduction gear mechanism where an inner gear rotates about a rotation axis while revolving around an eccentric axis which is disposed parallel to the rotation axis in a state where a drive shaft fitted in the inner gear is driven to rotate about the rotation axis, a biasing member provided at an outer periphery of the drive shaft and applying a biasing force to mesh an external teeth portion of the inner gear with an internal teeth portion of the ring gear, and a restriction portion provided at the drive shaft to restrict a displacement of the inner gear in a direction where the inner gear is separated from the ring gear against the biasing force of the biasing member. | 2018-12-27 |
20180371965 | FRUSTOCONICALLY SUPPORTED VALVE STEM SEAL ASSEMBLY - A valve stem seal assembly has an elastomeric seal with first and second radially inwardly directed sealing lips that are in intimate sealing contact with a valve stem. The assembly also has a metal seal retainer with a first metal seal retainer portion that has a surface axially slanted inward and downward from a top of the elastomeric seal. This slanted portion forms a metal frustoconical foundation with a second metal seal retainer portion that directly radially extends from the metal frustoconical foundation. The axially slanted inward surface of the metal retainer is directly radially outward from the radially inwardly directed first sealing lip. | 2018-12-27 |
20180371966 | DELIVERY DEVICE FOR A MOTOR VEHICLE - A delivery device for a motor vehicle for delivering oil from an oil sump to a lubricating oil circuit of internal combustion engine has, as an oil pump, a double-stroke vane-type pump with positive guidance of vanes. A direct drive of the vane-type pump by means of the internal combustion engine is configured for an operating point P | 2018-12-27 |
20180371967 | AIRCRAFT ENGINE LUBRICATION CIRCUIT AND METHOD, USING A NON-RETURN PRESSURISATION VALVE WITH TWO PLUGS - A non-return valve with twin plugs is connected to a fluid reservoir and equipment that can receive a small overflow quantity essentially in the gaseous state from the reservoir. This occurs when the primary valve is open. In the case of a larger overflow essentially in the liquid state, the openings are switched over to evacuate the overflow to another outlet branch of the non-return valve, without it being transferred to the equipment. The invention is useful in an oil lubrication circuit, in which a hypothetical fuel leak into the oil could cause the oil reservoir to overflow into the non-return valve and in which a significant flow of liquid to the equipment must be avoided; oil outlet through the other branch of the outlet can remain in a reservoir provided with a drain system. | 2018-12-27 |
20180371968 | Method of Controlling the Temperature of Oil for Vehicle Powertrain - A thermal management unit for a vehicle powertrain includes an integrated oil heater, a control valve, and a pressure relief valve. A remote oil cooler is connected to fluid ports of the thermal management unit. Transmission oil is received into the thermal management unit and is directed to one or both of the transmission oil heater and the transmission oil cooler. A portion of the flow of oil can be internally bypassed through the pressure relief valve to maintain the pressure of the oil below a threshold. The flow of oil is directed through the control valve after having been heated and/or cooled, and the proportions of oil being directed through the oil heater and the oil cooler are determined by the temperature of the oil in the control valve. | 2018-12-27 |
20180371969 | HEATED LUBRICATION CIRCUIT - A lubrication circuit for a gas turbine engine comprises a heat exchanger having an inlet pipe which carries a flow of lubricant to the heat exchanger; a heater configured to heat lubricant to produce a flow of heated lubricant to be provided to the heat exchanger; and a sensor operable to measure a measured parameter from which it can be determined whether the lubricant requires heating. | 2018-12-27 |
20180371970 | METHOD FOR SEPARATE LUBRICATION OF A DRIVE SYSTEM FOR A MOTOR VEHICLE - The present application concerns a method for separate lubrication of a drive system for a motor vehicle, the system including a compressor and an internal combustion engine including a top end and a bottom end that are coupled together, the method including: —lubricating the bottom end with a lubricating composition CL | 2018-12-27 |
20180371971 | FAULT DETECTION DEVICE FOR INTERNAL COMBUSTION ENGINE - A fault detection unit of an internal combustion engine includes a recirculation pipe connected with an upstream-side part of an intake pipe of the internal combustion engine upstream of a supercharger, the recirculation pipe to supply an evaporated fuel that is unburned and is generated in the internal combustion engine to the intake pipe, and a fault detection unit to detect a leakage occurrence of the recirculation pipe based on a crank-case inner pressure of the internal combustion engine when the internal combustion engine is operating in a specified operation condition that the crank-case inner pressure is a positive pressure. | 2018-12-27 |
20180371972 | Internal Combustion Engine with reduced noise and increased performance - This invention relates generally to a system for reducing the noise and increasing the performance of an internal combustion engine. More specifically, the invention is an apparatus and method of using the same which utilizes standard mechanics of the vehicle itself to achieve its objectives. While this invention is generally intended for engines mounted on bicycles, the principles apply to any motor vehicle equipped with spokes, wheels, or fans. | 2018-12-27 |
20180371973 | Exhaust gas after-treatment arrangement and method for operating such an arrangement - Exhaust gas after-treatment arrangement and method for operating an exhaust gas after-treatment arrangement | 2018-12-27 |
20180371974 | FLUID FOR PURIFYING HEAT ENGINES AND METHODS FOR PREPARING SAID FLUIDS BY EMULSIFICATION - The present invention describes a fluid which is suitable for the decontamination of heat engines which can carry out, at the same time, both the catalytic reduction of oxides of nitrogen (NOx) contained in exhaust gases and assist in the regeneration of the particulate filter (PF). The invention also describes several embodiments of said fluid consisting of producing an oil-in-water type emulsion. | 2018-12-27 |
20180371975 | COMBUSTION ENGINE EXHAUST GAS PURIFYING FACILITY - An exhaust gas purifying facility of a combustion engine includes: a marine combustion engine; a reducing device for feeding urea water into an exhaust gas in an exhaust gas line of the marine combustion engine; and a generation device for generating the urea water from urea powder. The generation device includes a storage-generation tank device and an adjustment tank device capable of adjusting the density of the urea water. The storage-generation tank device has a storage-generation tank for storing the urea powder and feeding water to the urea powder for dissolution. The adjustment tank device has an adjustment tank for storing the urea water withdrawn from the storage-generation tank. | 2018-12-27 |
20180371976 | Tank system for a reducing agent - A tank system for a reducing agent includes: a vessel configured to store the reducing agent, the vessel having: an upper vessel walk lateral vessel walls, and a lower vessel wall configured to form a base of the vessel; and a heating device disposed in the vessel. At least parts of the heating device are disposed in a part of the base of the lower vessel wall of the vessel. | 2018-12-27 |
20180371977 | Tank system for a reducing agent - A tank system for a reducing agent includes: a vessel configured to store the reducing agent, the vessel having: an upper vessel wall, lateral vessel walls, and a lower vessel wall; and a conveying device, the conveying device being configured to provide the reducing agent under pressure by way of an outlet to an exhaust gas. One or more openings are arranged in the lower vessel wall the one or more openings forming a connection to a further volume (V) filled with reducing agent. At least one opening of the one or more openings has radially inwardly directed elements arranged on a circumference of the at least one opening. | 2018-12-27 |
20180371978 | Impingement Mixer for Exhaust Treatment - A mixer assembly for treating exhaust with an injected reductant as the exhaust flows through an exhaust gas passageway includes a tubular shell and a rod. A first end and a second opposite end of the rod are fixed to the shell. The rod has a serpentine shape with a plurality of parallel extending portions interconnected by curved portions. The curved portions are positioned proximate an inner surface of the shell such that the rod traverses the exhaust passageway. The mixer assembly is positioned such that the rod is directly impinged by reductant injected into the exhaust gas passageway. | 2018-12-27 |
20180371979 | HEAT EXCHANGE MODULE - A heat exchange module has a restriction protrusion that is provided to protrude between a blade of a cooling fan and a core portion of a heat exchanger and that restricts the blade from approaching the core portion more than a predetermined position. In a state where one side of an outline of a rectangular shaped fan shroud is disposed so as to face an installation surface, the restriction protrusion is provided in a position where the amount of water reaching the cooling fan through the heat exchanger becomes greater than the amount of water at position just below a rotation axis of the cooling fan in a case where at least a portion of the fan shroud is submerged in water. | 2018-12-27 |
20180371980 | COOLING CONTROL SYSTEM FOR WORKING MACHINE AND THE WORKING MACHINE - A cooling control system includes a prime mover, a fan to be rotated under rotational power of an output shaft of the prime mover, a housing to which the fan is attached, a rotor to be rotated under rotational power of the prime mover, the rotor and the housing, under the agency of a fluid, rotating together, a fluid setting circuit to determine an injection quantity of the fluid to be introduced into the gap, a fan rotation detection device to detect a fan actual rotation speed, a target rotation obtaining circuit to obtain a fan target rotation speed. The integral controlling circuit does not execute the integral control with a difference between the fan actual rotation speed and a fan target rotation speed being greater than or equal to a threshold, and executes the integral control with the difference being less than the threshold. | 2018-12-27 |
20180371981 | System and Method Involving a Variable Speed Cooling Fan Used With a Compressor and an Internal Combustion Engine - A system and method of a variable speed cooling fan for a skid mounted compressor. A magnetic variable speed clutch is mounted to the cooling fan drive shaft. The clutch mechanism is driven via by a drive pulley on the crankshaft of the engine driving the compressor. The speed of the fan is varied dependent upon the temperature of the fluids being cooled. | 2018-12-27 |
20180371982 | THERMAL MANAGEMENT SYSTEMS, COOLANT VALVES AND CONTROL LOGIC FOR VEHICLE POWERTRAINS - Disclosed are two-valve, split-layout engine cooling systems, methods for making and method for operating such cooling systems, engine coolant valve assembly configurations, and vehicles equipped with an active thermal management system for cooling select powertrain components. A disclosed thermal management system includes a radiator for cooling coolant fluid, and a coolant pump for circulating coolant fluid received from the radiator. A set of conduits fluidly connect the coolant pump to an engine block, a cylinder head, and an exhaust manifold. Another set of conduits fluidly connect the engine block, cylinder head, and exhaust manifold to the radiator, coolant pump, and one or more oil heaters. A first valve assembly is operable to regulate coolant flow between the coolant pump and the radiator. A second valve assembly is operable to regulate coolant fluid flow, individually and jointly, between the engine block, cylinder head, exhaust manifold, radiator, coolant pump, and oil heater(s). | 2018-12-27 |
20180371983 | Motor Vehicle Turbo or Supercharger Diverter Valve System - Turbo or super charged intake tract diverter valve system, upstream of a throttle valve, includes a closure means ( | 2018-12-27 |
20180371984 | FORMAT-SPECIFIC BIDS BASED ON GOAL-ORIENTED TARGETING OF CONTENT - Methods, systems, and apparatus, including computer programs encoded on a computer-readable storage medium, including a method for determining bids for campaigns. The method comprises receiving an indication from a sponsor to create a video campaign and presenting a user interface for the sponsor to designate a goal for the video campaign. The goal is expressed in terms of a balance between maximizing any views versus engaged views. Engaged views arise when a user indicates their desire to view a video content item or where the user performs one or more actions related to the video content item while or after viewing the video content item. The method further comprises receiving a sponsor selection of a goal, receiving a maximum bid to be applied to all video campaign formats, automatically determining an adjusted maximum bid for each format based on the maximum bid and sponsor goal selection, and storing the campaign. | 2018-12-27 |
20180371985 | TURBOCHARGER - This turbocharger includes a rotating shaft extending along an axis, a turbine wheel provided at a first end portion of the rotating shaft, a compressor wheel provided at a second end portion of the rotating shaft, a housing accommodating at least a portion of the rotating shaft, bearings provided in the housing and configured to support the rotating shaft, supply flow paths supplying lubricating oil to the bearings, a discharge oil chamber formed in the housing and to which the lubricating oil is discharged from the bearings, and an oil drainage port formed below the discharge oil chamber, in which at least one of the discharge oil chamber and the oil drainage port is formed to be asymmetric between a first region and a second region defined by a vertical plane including the axis of the rotating shaft as a boundary plane. | 2018-12-27 |
20180371986 | CONNECTING ROD FOR AN INTERNAL COMBUSTION ENGINE WITH VARIABLE COMPRESSION - A connecting rod for a variable compression internal combustion engine, the connecting rod including a crank bearing eye configured to connect the connecting rod to a crankshaft of the variable compression internal combustion engine; a connecting rod bearing eye configured to connect the connecting rod to a cylinder piston of the variable compression internal combustion engine; an eccentrical element adjustment arrangement configured to adjust an effective connective rod length, which eccentrical element adjustment arrangement includes an eccentrical element that is connected torque proof with an eccentrical element lever, wherein a wrist pin of the cylinder piston is receivable in the eccentrical element, wherein the eccentrical element adjustment arrangement includes two hydraulic chambers respectively including a piston that is movably arranged in a cylindrical borehole and connected with a support rod which is connected with the eccentrical element lever at another end, wherein the support rod is configured from plural components. | 2018-12-27 |
20180371987 | SWITCH VALVE FOR CONTROLLING A HYDRAULIC FLUID FLOW FOR A CONNECTING ROD OF VARIABLE COMPRESSION INTERNAL COMBUSTION ENGINE AND CONNECTING ROD - A switch valve for controlling a hydraulic fluid flow of a connecting rod for an internal combustion engine with variable compression with an eccentrical element adjustment arrangement for adjusting an effective connecting rod length, the eccentrical element adjustment arrangement including a first cylinder including a first hydraulic chamber; a second cylinder including a second hydraulic chamber, wherein the first cylinder includes a first inlet for feeding hydraulic fluid into the first cylinder from a supply and the second cylinder includes a second inlet for feeding hydraulic fluid into the second cylinder from the supply, wherein the first cylinder includes a first drain for draining the hydraulic fluid from the first cylinder and the second cylinder includes a second drain for draining the hydraulic fluid from the second cylinder, wherein the switch valve includes a step piston which is displaceable into a first switching position or a second switching position, | 2018-12-27 |
20180371988 | LENGTH-ADJUSTABLE CONNECTING ROD WITH ELECTROMAGNETICALLY-ACTUATABLE SWITCHING VAVLE - The invention relates to a length-adjustable connecting rod for a reciprocating piston engine, particularly a reciprocating piston internal combustion engine, comprising a hydraulic arrangement with which a length of the connecting rod can be adjusted, and a switching valve for controlling the inflow and outflow of a hydraulic medium into or out of the hydraulic arrangement, wherein the switching valve can be actuated electromagnetically. | 2018-12-27 |
20180371989 | FUEL INJECTION STRATEGIES IN OPPOSED-PISTON ENGINES WITH MULTIPLE FUEL INJECTORS - In an opposed-piston engine, two or more fuel injectors are mounted to a cylinder for direct side injection into the cylinder. The injectors are controlled so as to inject either a single fuel pulse or a plurality of fuel pulses per cycle of engine operation in order to initiate combustion during varying engine speeds and operating conditions. | 2018-12-27 |
20180371990 | ENGINE OPERABLE IN HORIZONTAL AND VERTICAL SHAFT ORIENTATIONS - A small air-cooled internal combustion engine includes an aluminum engine block including a cylinder extending along a longitudinal cylinder axis and a block mounting surface, a piston configured to reciprocate within the cylinder, a crankshaft coupled to the piston and configured to rotate about a crankshaft axis in response to reciprocation of the piston, and an aluminum crankcase cover including a cover mounting surface. The block mounting surface contacts the cover mounting surface. The block mounting surface and the cover mounting surface are both positioned at an angle to the crankshaft axis and the angle is not 90 degrees. | 2018-12-27 |
20180371991 | AIRCRAFT INCORPORATING A LOW-TEMPERATURE BLEED SYSTEM - An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced. | 2018-12-27 |
20180371992 | EXHAUST MANIFOLD SYSTEM FOR TURBOCHARGER DEVICE WITH PLURAL VOLUTE MEMBERS - A turbocharger system includes a manifold system that maintains separation between flow paths of different manifold arrangements. One manifold arrangement directs flow from a first group of combustion chambers to a first volute passage of a turbine section of a turbocharger. Another manifold arrangement directs flow from a second group of combustion chambers to a second volute passage of the turbine section of the turbocharger. The system also provides selective variation of the available volume for exhaust flow through the manifold arrangements. | 2018-12-27 |
20180371993 | SYSTEM AND METHOD FOR LIQUID AIR ENERGY STORAGE - A liquid air energy storage system, the system comprising: a liquid air storage means; an input of a first pump in fluid communication with the liquid air storage means; a first heat exchanger in fluid communication with an output of the first pump; a second heat exchanger in fluid communication first heat exchanger and configured to receive the fluid stream from the first pump and the first heat exchanger; a first expander turbine generator in fluid communication with the second heat exchanger; the first heat exchanger in fluid communication with the first expander turbine generator; a third heat exchanger in fluid communication with the first heat exchanger and configured to receive the fluid stream from the first expander turbine generator and the first heat exchanger; a second expander turbine generator in fluid communication with the third heat exchanger; the first heat exchanger in fluid communication with the second expander turbine generator; the fluid stream from second expander turbine generator and first heat exchanger in fluid communication with ambient atmosphere; a refrigerant stream in fluid communication with a third expander turbine generator; a fourth heat exchanger in fluid communication with the third expander turbine generator; a fourth expander turbine generator in fluid communication with the fourth heat exchanger; a fifth heat exchanger in fluid communication with the fourth expander turbine generator; the first heat exchanger in fluid communication with the fifth heat exchanger; an input of a second pump in fluid communication with the first heat exchanger, and configured to receive the refrigerant stream from the fifth heat exchanger and the and the first heat exchanger; the first heat exchanger in fluid communication with the output of the second pump; a sixth heat exchanger in fluid communication with the first heat exchanger, and configured to receive the refrigerant stream from the output of the second pump and the first heat exchanger; and the third expander turbine generator in fluid communication with the sixth heat exchanger. A liquid air energy storage system, the system comprising: a liquid air storage means; an input of a first pump in fluid communication with the liquid air storage means; a first heat exchanger in fluid communication with an output of the first pump; a second heat exchanger in fluid communication first heat exchanger and configured to receive the fluid stream from the first pump and the first heat exchanger; a first expander turbine generator in fluid communication with the second heat exchanger; the first heat exchanger in fluid communication with the first expander turbine generator; a third heat exchanger in fluid communication with the first heat exchanger and configured to receive the fluid stream from the first expander turbine generator and the first heat exchanger; a second expander turbine generator in fluid communication with the third heat exchanger; the first heat exchanger in fluid communication with the second expander turbine generator; the fluid stream from second expander turbine generator and first heat exchanger in fluid communication with ambient atmosphere; a refrigerant stream in fluid communication with a third expander turbine generator; a fourth heat exchanger in fluid communication with the third expander turbine generator; a fourth expander turbine generator in fluid communication with the fourth heat exchanger; a fifth heat exchanger in fluid communication with the fourth expander turbine generator; the first heat exchanger in fluid communication with the fifth heat exchanger; a seventh heat exchanger in fluid communication with the first heat exchanger, and configured to receive the refrigerant stream from the fifth heat exchanger and the and the first heat exchanger; an input of a second pump in fluid communication with the seventh heat exchanger; the first heat exchanger in fluid communication with the output of the second pump; a phase separator in fluid communication with the first heat exchanger, and configured to receive the refrigerant stream from the output of the second pump and the first heat exchanger; a liquid refrigerant stream exiting the phase separator and in fluid communication with the first heat exchanger; the liquid refrigerant vaporizing due to the first heat exchanger and becoming a second vapor refrigerant stream; a sixth heat exchanger in fluid communication second vapor refrigerant stream; the third expander turbine generator in fluid communication with the sixth heat exchanger; and a first vapor refrigerant stream exiting the phase separator and in fluid communication with the sixth heat exchanger. A method for liquid air energy storage, the method comprising: pumping a liquid air stream in a first pump; exchanging heat with the liquid air stream in a first heat exchanger so the liquid air becomes vapor air stream; removing energy from the vapor air stream in a second heat exchanger; driving a first expander turbine generator with the vapor air stream and generating a first amount of electricity; cooling the vapor air stream from the first expander turbine generator in the first heat exchanger; removing energy from the vapor air stream from the first heat exchanger and from the first expander turbine generator in a third heat exchanger; driving a second expander turbine generator with the vapor air stream and generating a second amount of electricity; exchanging heat with the vapor air stream from the second expander turbine generator in the first heat exchanger and then releasing the vapor air stream to the ambient atmosphere; driving a third expander turbine generator with a refrigerant vapor stream and generating a third amount of electricity; removing energy from the refrigerant vapor stream in a fourth heat exchanger; driving a fourth expander turbine generator with the refrigerant vapor stream from the fourth heat exchanger and generating a fourth amount of electricity; removing energy from the refrigerant vapor stream in a fifth heat exchanger; exchanging energy with the refrigerant vapor stream in the first heat exchanger; pumping the refrigerant vapor stream in a second pump; exchanging energy with the refrigerant vapor stream from the second pump in the first heat exchanger; and exchanging energy with the refrigerant vapor stream from the first heat exchanger and second pump in a sixth heat exchanger. A liquid air energy storage system, the system comprising: pumping a liquid air stream in a first pump; exchanging heat with the liquid air stream in a first heat exchanger so the liquid air becomes vapor air stream; removing energy from the vapor air stream in a second heat exchanger; driving a first expander turbine generator with the vapor air stream and generating a first amount of electricity; cooling the vapor air stream from the first expander turbine generator in the first heat exchanger; removing energy from the vapor air stream from the first heat exchanger and from the first expander turbine generator in a third heat exchanger; driving a second expander turbine generator with the vapor air stream and generating a second amount of electricity; exchanging heat with the vapor air stream from the second expander turbine generator in the first heat exchanger and then releasing the vapor air stream to the ambient atmosphere; driving a third expander turbine generator with a refrigerant vapor stream and generating a third amount of electricity; removing energy from the refrigerant vapor stream in a fourth heat exchanger; driving a fourth expander turbine generator with the refrigerant vapor stream from the fourth heat exchanger and generating a fourth amount of electricity; removing energy from the refrigerant vapor stream in a fifth heat exchanger; exchanging energy with the refrigerant vapor stream in the first heat exchanger; exchanging energy with the refrigerant vapor stream in a seventh heat exchanger; pumping the refrigerant vapor stream in a second pump; exchanging energy with the refrigerant vapor stream from the second pump in the first heat exchanger and creating a refrigerant liquid vapor stream; separating a refrigerant vapor stream and refrigerant liquid stream from the refrigerant liquid vapor stream in a phase separator; exchanging energy with the refrigerant liquid stream from the phase separator in the first heat exchanger, changing the refrigerant liquid stream to a refrigerant vapor stream; exchanging energy with the refrigerant vapor stream from the first heat exchanger and phase separator in a sixth heat exchanger; and exchanging energy with the refrigerant vapor stream directly from the phase separator in the sixth heat exchanger. | 2018-12-27 |
20180371994 | PARALLEL COMBUSTOR CONFIGURATION FOR UNMANNED UNDERWATER VEHICLE PROPULSION TURBINE - A propulsion system for an unmanned underwater vehicle includes at least one fuel storage tank. A plurality of combustors is connected to the at least one fuel storage tank. Each of the combustors is connected to a turbine via a corresponding nozzle. An output shaft is connected to the turbine and configured to output rotational energy from the turbine. | 2018-12-27 |
20180371995 | ROTATING DEVICES FOR MITIGATION OF ADVERSE FLOW CONDITIONS IN AN ULTRA-SHORT NACELLE INLET - A flow control system on an aircraft engine nacelle incorporates a plurality of flow control devices each having a body. A second plurality of actuators is coupled to the body of an associated one of the flow control devices. The actuator rotates the body about a leading edge of an inlet of a nacelle from a retracted position to an extended position. | 2018-12-27 |
20180371996 | TRANSLATING TURNING VANES FOR A NACELLE INET - A flow control system on an aircraft engine nacelle incorporates a plurality of translating turning vanes each having a body. An equal plurality of actuators is coupled to a trailing edge of the body of an associated one of the translating turning vanes. The actuator translates the body from a retracted position to an extended position. | 2018-12-27 |
20180371997 | CLEARANCE CONTROL DEVICE - A clearance control system includes one or more clearance control devices that include features for controlling the clearances between rotating and stationary components of an engine. In one exemplary aspect, a clearance control device utilizes a fluid to pressurize an actuation chamber defined by a compliant member of the clearance control device. The pressurization of the actuation chamber causes the actuation chamber to expand in a direction that changes the clearance between the stationary and rotating components of the engine. | 2018-12-27 |
20180371998 | DAMPER CHECK VALVE - A gas turbine engine includes a fan, a compressor, a combustor, a turbine, a bypass duct, and a bearing compartment assembly. The bearing compartment assembly includes a fluid pump, a compartment, a fluid line between the fluid pump and the compartment, and a damper check valve located in the fluid line. The damper check valve is a unitary, monolithic component that is configured to restrict a reverse flow from the compartment to the fluid pump substantially more than the damper check valve restricts a standard flow from the fluid pump to the compartment. | 2018-12-27 |
20180371999 | COOLING SYSTEM FOR A TURBINE ENGINE - A cooling system for a turbine engine is provided. The turbine engine includes a compressor, a compressor discharge chamber (CDC), a combustor assembly, and a turbine coupled in a serial flow relationship such that a first portion of air from the CDC is channeled to the combustor assembly. The turbine is coupled to the compressor via a rotor. The cooling system includes an air duct configured to channel a second portion of air from the CDC to a mid-rotor region of the rotor, and a fluid supply system coupled to the air duct at a coupling. The fluid supply system is configured to channel a flow of fluid to the coupling. The coupling is configured to cool the second portion of CDC air via absorption of heat by the fluid from the second portion of CDC air. | 2018-12-27 |
20180372000 | GAS TURBINE COOLING SYSTEM, GAS TURBINE FACILITY INCLUDING THE SAME, AND CONTROL DEVICE AND CONTROL METHOD OF GAS TURBINE COOLING SYSTEM - A gas turbine cooling system includes: a cooling air line that guides compressed air; a cooler that cools the compressed air; a flow rate adjuster that adjusts the flow rate of the cooling air; and a control device. The control device includes: a load change determination unit that determines whether a load indicated by a load command of the gas turbine has changed; a first command generation section that generates a first command indicating such an operation amount of the flow rate adjuster as allows the flow rate of the cooling air to meet a target flow rate; and a second command generation section that, when it is determined that the load indicated by the load command has changed, generates a second command indicating such an operation amount of the flow rate adjuster as allows a change-adapted flow rate higher than the target flow rate to be met. | 2018-12-27 |
20180372001 | TURBOJET ENGINE WITH A MEANS OF REACTING THRUST ON THE INTER-COMPRESSORS CASING - A multi-flow turbojet engine generally includes an upstream ducted fan driven by a gas generator, the gas generator having a first and a second compressor, which are coaxial, an inlet case forming a support for the rotors of the upstream ducted fan and of the first compressor, an inter-compressor case downstream of the inlet casing and forming a support for the rotors of the second compressor, attachment means for thrust take-up rods, which attachment means are arranged on the inter-compressor case. The turbojet engine includes at least one axial stress transmission rod for connecting the inlet case to the inter-compressor case. | 2018-12-27 |
20180372002 | COOLING SYSTEM FOR EMISSION GASES OF AN ELECTRONICALLY CONTROLLED ENGINE - This invention relates to a cooling system for an internal combustion engine, and is particularly suitable for cooling emission gases from electronically controlled, Tier 3 fuel injection engines [ | 2018-12-27 |
20180372003 | PROPULSION SYSTEM FOR AN AIRCRAFT - A hybrid-electric propulsion system includes an electric machine coupled to a rotating system of the turbomachine and an electric energy storage unit, the electric machine electrically coupled to an electric power source. A method for operating the turbomachine of a hybrid-electric propulsion system includes providing electrical power from the electric machine to the electric energy storage unit during a flight operation mode of the turbomachine, the turbomachine rotating the electric machine to generate electrical power during the flight operating mode; determining the turbomachine is in a post flight operation mode or in a pre-flight operation mode; and providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine to prevent or correct a bowed rotor condition. | 2018-12-27 |
20180372004 | COMPACT ACCESSORY SYSTEMS FOR A GAS TURBINE ENGINE - An accessory system for a gas turbine engine having a driveshaft with an axis of rotation is provided. The accessory system includes a towershaft coupled to the driveshaft and driven by the driveshaft along a towershaft axis of rotation. The accessory system also includes a shaft including a first shaft bevel gear coupled to a towershaft bevel gear. The shaft is rotatable by the towershaft along a shaft axis of rotation. The shaft axis of rotation is transverse to the towershaft axis of rotation. The accessory system includes a first accessory drive shaft having a first accessory bevel gear driven by the shaft. The accessory system also includes a second accessory drive shaft having a second accessory bevel gear driven by the shaft. A first accessory axis of rotation and a second accessory axis of rotation are substantially transverse to the shaft axis of rotation. | 2018-12-27 |
20180372005 | GAS TURBINE ENGINE GEARED COMPRESSOR WITH FIRST AND SECOND INPUT ROTORS - A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The first and second rotor assemblies are arranged to undergo relative rotation in use about a common axis. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies. | 2018-12-27 |
20180372006 | FLUID SUPPLY SYSTEM FOR TURBINE ENGINE, INCLUDING AN ADJUSTABLE FLOW PUMP AND A FLUID METERING DEVICE - A fluid supply system ( | 2018-12-27 |
20180372007 | METHODS AND SYSTEM FOR A THROTTLE - Methods and systems are provided for a vacuum generating throttle. In one example, a method may include pivoting the throttle based on a desired airflow rate and/or vacuum replenishment, where the airflow rate and/or vacuum replenishment are adjusted based on one or more passages arranged interior to the throttle. | 2018-12-27 |
20180372008 | Method For Determining The Composition Of The Fuel Used To Operate An Internal Combustion Engine - A method for operating an internal combustion engine may include: measuring dynamic pressure oscillations in the inlet tract at a defined operating point during normal operation; generating a corresponding pressure oscillation signal; determining a crankshaft phase angle; determining an actual phase position using the pressure oscillation signal by discrete Fourier transformation; determining a chemical composition of the fuel using the determined actual phase position and reference phase positions of the same signal frequency for different fuel compositions; and adjusting operating parameters of the internal combustion engine based on the determined chemical composition. | 2018-12-27 |
20180372009 | Method For Determining The Composition Of The Fuel Used And Operating An Internal Combustion Engine - An example method for operating an internal combustion engine may include: measuring pressure oscillations for a cylinder in the inlet tract at a defined operating point during normal operation; generating a corresponding oscillation signal; determining a crankshaft phase angle corresponding to the oscillation signal; and from the pressure oscillation signal, using discrete Fourier transformation to calculate the actual phase position of a selected signal frequency; determining a further comparison phase position in the same way from the selected signal frequency in the absence of fuel injection; calculating an actual phase position difference; on the basis of the difference, taking into consideration reference phase position differences of the same signal frequency for different fuel compositions, to identify a fuel composition of the presently used fuel; and adapting operating parameters of the engine based on the identified composition. | 2018-12-27 |
20180372010 | METHOD FOR PRECISE SYNCHRONIZATION OF A COMBUSTION ENGINE - An exact synchronization method for determining an angular position of an engine, modulo one engine cycle, by a crankshaft sensor and of at least one camshaft sensor. The method includes: estimating a continuous estimated interval assumed to contain the angular position, on receipt of a “marker” event, determining an angular position corresponding to each one of the possible occurrences of this “marker”, comparing the determined angular position with the estimated interval. If exactly one of the determined angular positions belongs to the estimated interval, then this angular position is the angular position of the engine. And an engine control method using such a method. | 2018-12-27 |
20180372011 | CONTROLLER AND CONTROL METHOD FOR INTERNAL COMBUSTION ENGINE - To provide a controller and a control method for an internal combustion engine capable of estimating exhaust gas temperature at any estimation positions of the exhaust pipe with good accuracy by taking into consideration a temperature drop of exhaust gas by heat radiation of the exhaust pipe. A controller for an internal combustion engine is provided with an outlet gas temperature calculator that calculates an outlet gas temperature which is a temperature of exhaust gas at an outlet of a combustion chamber, based on the driving condition; a heat radiation amount calculator that calculates a temperature decrease amount of the exhaust gas by heat radiation of an exhaust pipe from the outlet of the combustion chamber to an estimation position; and an exhaust gas temperature estimation calculator that estimate an exhaust gas temperature at the estimation position by subtracting the temperature decrease amount from the outlet gas temperature. | 2018-12-27 |
20180372012 | EXHAUST GAS CONTROL APPARATUS FOR INTERNAL COMBUSTION ENGINE - An exhaust gas control apparatus includes a fuel injection device, a NOx occlusion reduction catalyst, a fuel addition valve, an inflow gas adjustment device, and an electronic control unit. The electronic control unit executes a low flow rate reduction treatment for removing NO | 2018-12-27 |