Patent application number | Description | Published |
20080229756 | SYSTEM AND METHOD FOR PASSIVE VALVING FOR PULSE DETONATION COMBUSTORS - A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device. | 09-25-2008 |
20080310981 | POSITIVE DISPLACEMENT FLOW SEPARATOR - A positive displacement flow separator contains a rotor portion positioned inside a casing portion to act as a least area rotor which captures a volume and moves the volume along the length of the separator. The rotor portion contains a plurality of lobes which interact with grooves in the casing portion, such that the interaction of the lobes and grooves create barriers which capture the volume The creation of the volume creates a flow barrier between a downstream end of the separator and an upstream end of the separator. The flow separator is coupled to a combustion portion to provide a flow of material to the combustion portion. | 12-18-2008 |
20080310982 | POSITIVE DISPLACEMENT FLOW SEPARATOR WITH COMBUSTOR - A positive displacement flow separator or combustor contains a rotor portion positioned inside a casing portion to act as a least area rotor which captures a volume and moves the volume along the length of the separator. The rotor portion contains a plurality of lobes which interact with grooves in the casing portion, such that the interaction of the lobes and grooves create barriers which capture the volume. The creation of the volume creates a flow barrier between a downstream end of the separator and an upstream end of the separator. | 12-18-2008 |
20090133377 | MULTI-TUBE PULSE DETONATION COMBUSTOR BASED ENGINE - An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is positioned such that the inlet portion of the pulse detonation combustor is located forward of an outlet of the compressor stage with respect to the engine. The pulse detonation combustor is angled with respect to a centerline of the engine. | 05-28-2009 |
20090139199 | PULSE DETONATION COMBUSTOR VALVE FOR HIGH TEMPERATURE AND HIGH PRESSURE OPERATION - A pulse detonation combustor valve assembly contains at least one pulse detonation combustor having an inlet portion through which air and/or fuel enters the chamber of the combustor. An annular rotating valve portion is positioned adjacent to an outer surface of the pulse detonation combustor and concentrically with the pulse detonation combustor so that the annular rotating valve portion can be rotated with respect to the combustor. The annular rotating valve portion contains at least one inlet portion through which air and/or fuel passes to enter the inlet portion of the pulse detonation combustor. | 06-04-2009 |
20090139203 | METHOD AND APPARATUS FOR TAILORING THE EQUIVALENCE RATIO IN A VALVED PULSE DETONATION COMBUSTOR - A pulse detonation combustor assembly contains at least one PDC tube, a mechanical air flow valve which directs an air flow into the PDC tube, where the mechanical air flow assembly changes a rate of the air flow into the PDC tube during a fill stage of the PDC tube. The assembly also contains a fuel flow control valve which directs fuel to the PDC tube and changes the rate of the fuel flow into PDC tube. By controlling the flow of the fuel and air into the PDC tube the equivalence ratio profile of the PDC tube can be tailored and controlled. | 06-04-2009 |
20090220368 | POSITIVE DISPLACEMENT CAPTURE DEVICE AND METHOD OF BALANCING POSITIVE DISPLACEMENT CAPTURE DEVICES - A positive displacement capture apparatus contains a plurality of positive displacement capture devices which each contain a rotor portion positioned inside a casing portion to act as a least area rotor which captures a volume and moves the volume along the length of the separator. The rotor portion contains a plurality of lobes which interact with grooves in the casing portion, such that the interaction of the lobes and grooves create barriers which capture the volume. The creation of the volume creates a flow barrier between a downstream end of the separator and an upstream end of the separator. The flow separator is coupled to a combustion portion to provide a flow of material to the combustion portion. The plurality of positive displacement capture devices are positioned, oriented and rotational timed such that eccentric loads created by the rotation of the rotor portions cancel each other out during operation. | 09-03-2009 |
20090220369 | NON-CONTACT SEAL FOR POSITIVE DISPLACEMENT CAPTURE DEVICE - A positive displacement capture device contains a rotor portion positioned inside a casing portion to act as a least area rotor which captures a volume and moves the volume along the length of the separator. The rotor portion contains a plurality of lobes which interact with grooves in the casing portions such that the interaction of the lobes and grooves create barriers which capture the volume. The creation of the volume creates a flow barrier between a downstream end of the separator and an upstream end of the separator. The flow separator is coupled to a combustion portion to provide a flow of material to the combustion portion. There is a non-contact seal between the lobes and the grooves, and the lobes have channels or depressions at their ends. | 09-03-2009 |
20090241507 | GROUND BASED PULSE DETONATION COMBUSTOR FOR POWER GENERATION - A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a regenerator is positioned between the compressor stages and the combustion stage. The combustion stage contains at least one of a pulse detonation combustor and constant volume combustor. Downstream of the combustion stage is the turbine stage. Heat for the regenerator is supplied from the turbine stage. Further, a bypass flow device is included which re-directs flow upstream of the combustion stage to downstream of the combustion stage and upstream of the turbine stage. | 10-01-2009 |
20090266047 | MULTI-TUBE, CAN-ANNULAR PULSE DETONATION COMBUSTOR BASED ENGINE WITH TANGENTIALLY AND LONGITUDINALLY ANGLED PULSE DETONATION COMBUSTORS - An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine. | 10-29-2009 |
20100071458 | POSITIVE DISPLACEMENT FLOW MEASUREMENT DEVICE - A positive displacement flow measurement device includes a rotor portion positioned inside a casing portion to act as a least area rotor that captures a volume of material and moves the volume of material along the length of the device. The device is coupled to a means for counting the number of revolutions of the rotor portion and/or the casing portion over a predetermined period of time. In one embodiment, the counting means comprises a shaft encoder that measures the angular position of a shaft of the rotor portion and sends a signal to a processor of a computing device that determines the volume of material flowing through the device. | 03-25-2010 |
20100154380 | Control system for a land-based simple cycle hybrid engine for power generation - A pulse detonation combustor (PDC)-based hybrid engine control system includes a programmable controller directed by algorithmic software to control a rotational shaft speed of the PDC-based hybrid engine, an air inlet valve rotational speed for the PDC, and a fuel fill time period for the PDC in response to a corresponding low pressure turbine (LPT) shaft speed signal or a power difference signal based on a difference between desired power and actual power produced by the PDC-based hybrid engine and further in response to a fuel fill time signal for the PDC, such that a desired fuel fill fraction and stoichiometric ratio are maintained and further such that a mass air flowrate from an air compressor matches a mass air flowrate ingested via the PDC while the PDC-based hybrid engine is operating in an acceleration mode or a deceleration mode. | 06-24-2010 |
20100192536 | GROUND-BASED SIMPLE CYCLE PULSE DETONATION COMBUSTOR BASED HYBRID ENGINE FOR POWER GENERATION - An engine contains a compressor stage, a compressor plenum, an inlet valving stage, a PDC stage, a PDC exit nozzle stage, a transition stage, a high pressure turbine stage, a turbine plenum, and a low pressure turbine stage. The PDC stage contains at least one pulse detonation combustor and each of the compressor plenum, PDC exit nozzle stage and turbine plenum contain a volume used to reduce and/or widen pressure peaks generated by the operation of the PDC stage. | 08-05-2010 |
20100236214 | ROTARY AIR VALVE FIRING PATTERNS FOR RESONANCE DETUNING - An engine contains a compressor stage, a plurality of pulse detonation combustors and a rotary inlet valve structure having a plurality of inlet ports through which at least air flows to enter the pulse detonation combustors during operation of the engine. Downstream of the pulse detonation combustors is a turbine stage. Further, the ratio of the pulse detonation combustors to the inlet ports is a non-integer. | 09-23-2010 |
20100242436 | MODULATION OF INLET MASS FLOW AND RESONANCE FOR A MULTI-TUBE PULSE DETONATION ENGINE SYSTEM USING PHASE SHIFTED OPERATION AND DETUNING - An engine contains a compressor stage, a plurality of pulse detonation combustors and a plurality of inlet valves, where the inlet valves direct a mass flow into the pulse detonation combustors. A control system controls at least one of a phase shift, firing frequency and a τ | 09-30-2010 |
20110047961 | PULSE DETONATION INLET MANAGEMENT SYSTEM - A pulse detonation combustor valve assembly is provided that includes a fixed valve portion having an inlet and a reciprocating valve portion. The valve assembly is coupled to a pulse detonation combustor. The reciprocating valve portion is exterior to the fixed valve portion and coaxially aligned with the fixed valve portion. The reciprocating valve portion is arranged to reciprocate with respect to the fixed valve portion to control inlet flow through the inlet of the valve assembly. | 03-03-2011 |
20110047962 | PULSE DETONATION COMBUSTOR CONFIGURATION FOR DEFLAGRATION TO DETONATION TRANSITION ENHANCEMENT - According to one aspect of the invention, a pulse detonation combustor chamber is provided having an ignition chamber and a detonation chamber. The cross-sectional area of the ignition chamber is greater than the cross-sectional area of the detonation chamber. A flame is generated in the ignition chamber upon ignition of a flammable mixture. The flame flows into the detonation chamber and detonates within the detonation chamber. | 03-03-2011 |
20110126510 | PULSE DETONATION COMBUSTOR - In one embodiment, a pulse detonation combustor includes a gas discharge annulus including multiple nozzles engaged with one another via mating surfaces to support the gas discharge annulus in a circumferential direction. The pulse detonation combustor also includes multiple pulse detonation tubes extending to the nozzles. | 06-02-2011 |
20110126511 | THRUST MODULATION IN A MULTIPLE COMBUSTOR PULSE DETONATION ENGINE USING CROSS-COMBUSTOR DETONATION INITIATION - A method and apparatus for modulating the thrust during a flight envelope of a multiple combustor chamber detonation engine using cross-combustor chamber detonation initiation are provided. The detonation combustor chambers are filled with a combustible mixture of fuel and oxidizer. The combustible mixture in one of the detonation combustor chambers is ignited by an ignition source, and the remaining detonation combustor chambers are ignited by detonation cross-firing via connectors. A controller controls the ignition source and the supply of oxidizer and fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope. | 06-02-2011 |
20110127456 | ROTATING VALVE ASSEMBLY FOR HIGH TEMPERATURE AND HIGH PRESSURE OPERATION - A rotating valve assembly includes an inner cup having at least one inlet port; an outer cup having at least one inlet port, the outer cup rotatably mounted concentric with the inner cup by a bearing arrangement; and a cooling system located between the inner cup and the bearing arrangement for providing a thermal barrier between the inner cup and the bearing arrangement. The valve assembly also includes a labyrinth sealing arrangement located around the at least one inlet port of one of the inner and outer cups for preventing leakage of pressure waves generated by detonations or quasi-detonations within a combustion chamber of the inner cup. | 06-02-2011 |
20110146232 | CONTROL SYSTEM FOR A PULSE DETONATION TURBINE ENGINE - A pulse detonation turbine engine (PDTE) includes at least one controllable multi-tube pulse detonation combustor (PDC) configured to initiate firing of one or more pulse detonation tubes in response to operation of a plurality of controllable peripheral PDC components to regulate PDTE output characteristics. A control system including a programmable controller directed by algorithmic software operates to generate control inputs for the plurality of controllable peripheral PDC components in response to PDTE input conditions, such that one or more PD tube controllable inputs can be different for at least one PD tube relative to another PD tube within the multi-tube PDC, and further such that detonation timing can be different for at least one PD tube relative to another PD tube within the multi-tube PDC. | 06-23-2011 |
20110146285 | PULSE DETONATION SYSTEM WITH FUEL LEAN INLET REGION - In one embodiment, a pulse detonation system includes a pulse detonation tube and an air valve disposed at an upstream end of the pulse detonation tube. The air valve is configured to provide an air flow into the pulse detonation tube. The pulse detonation system also includes a fuel injector configured to inject fuel into the air flow to establish a fuel-air mixture configured to support detonation, and to establish a region in the fuel-air mixture having a fuel to air ratio insufficient to support a detonation wave. The pulse detonation system further includes an ignition source configured to detonate the fuel-air mixture when the region is disposed adjacent to the air valve. | 06-23-2011 |
20110214407 | PULSE DETONATION SYSTEM - In one embodiment, a pulse detonation system includes a pulse detonation tube including a base tube and a thermally protective layer disposed adjacent to an inner surface of the base tube. The thermally protective layer is configured to limit temperature fluctuations at the inner surface of the base tube to less than approximately 20 degrees Celsius during operation of the pulse detonation system, and the thermally protective layer does not comprise a ceramic coating. | 09-08-2011 |
20120079806 | PULSE DETONATION TUBE WITH LOCAL FLEXURAL WAVE MODIFYING FEATURE - In one embodiment, a pulse detonation tube includes a continuous base tube having a substantially uniform wall thickness. The pulse detonation tube also includes a local flexural wave modifying feature configured to locally vary a flexural wave speed such that the flexural wave speed through the pulse detonation tube is different than an expected detonation wave speed, and/or to locally dissipate flexural wave energy. | 04-05-2012 |
20120102961 | Side-Initiated Augmentor for Engine Applications - A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath. | 05-03-2012 |
20120122039 | PULSE DETONATION COMBUSTOR - A pulse detonation combustor including a plurality of nozzles engaged with one another via mating surfaces to support a gas discharge annulus in a circumferential direction. The pulse detonation combustor also including multiple pulse detonation tubes extending for the nozzles and a plurality of thermal expansion control joints coupled to the plurality of pulse detonation tubes. Each of the plurality of thermal expansion control joints is configured to facilitate independent thermal growth of each of the plurality of pulse detonation tubes. The thermal expansion control joints may be configured as a bellows expansion joint or a sliding expansion joint. | 05-17-2012 |
20120131899 | INTEGRATED DEFLAGRATION-TO-DETONATION OBSTACLES AND COOLING FLUID FLOW - A detonation chamber and a pulse detonation combustor including a detonation chamber, wherein the detonation chamber includes a plurality of initiation obstacles and at least one injector in fluid flow communication with each of the plurality of initiation obstacles. The plurality of initiation obstacles are disposed on at least a portion of an inner surface of the detonation chamber with each of the plurality of initiation obstacles defining a low pressure region at a trailing edge. The plurality of initiation obstacles are configured to enhance a turbulence of a fluid flow and flame acceleration through the detonation chamber. The at least one injector in provides a cooling fluid flow to each of the plurality of initiation obstacles, wherein the cooling fluid flow is one of a fuel, a combination of fuels, air, or a fuel/air mixture. | 05-31-2012 |
20120131901 | SYSTEM AND METHOD FOR CONTROLLING A PULSE DETONATION ENGINE - In one embodiment, a pulse detonation engine (PDE) includes a controller configured to receive signals indicative of at least one of a desired operating parameter of the PDE and a measured internal parameter of the PDE, and to adjust at least one of a first fluid flow through the PDE and a second fluid flow through at least one of multiple pulse detonation tubes disposed within the PDE based on the signals. The PDE does not include a turbine or a mechanical compressor. | 05-31-2012 |
20120144798 | FLUIDIC DEFLAGRATION-TO-DETONATION INITIATION OBSTACLES - A detonation chamber and a pulse detonation combustor including a detonation chamber, wherein the detonation chamber includes a plurality of aerodynamic jets disposed adjacent an exterior of a sidewall of the detonation chamber. The detonation chamber further includes a plurality of openings formed in the sidewall of the detonation chamber, wherein each of the plurality of openings is in fluidic communication with one of the plurality of aerodynamic jets. The plurality of aerodynamic jets are adapted to create a plurality of jet flows of a fluid within the detonation chamber during a combustion cycle defining a plurality of initiation obstacles within the detonation chamber to enhance a turbulence of a fluid flow and flame acceleration through the detonation chamber. | 06-14-2012 |
20120151895 | HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS - The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass includes a pump that raises the pressure of the bypass flow sufficient to deliver it to downstream stations of the engine that contain combustion products that are at a higher pressure than the compressor exit. | 06-21-2012 |
20120151896 | HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS - The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted. | 06-21-2012 |
20120192630 | Pulse Detonation Turbine Engine Using Turbine Shaft Speed for Monitoring Combustor Tube Operation - The present application provides a shaft speed monitoring system for a pulse detonation combustor with a number of combustion tubes and positioned about a shaft of a pulse detonation turbine engine. The shaft speed monitoring system may include one or more shaft sensors positioned about the shaft and a control in communication with the shaft sensors to determine a number of shaft speed fluctuations related to each of the combustion tubes. | 08-02-2012 |
20130042595 | PULSE DETONATION COMBUSTOR WITH PLENUM - A pulse detonation combustor includes at least one plenum located along the length of the pulse detonation combustor. The plenum can be located: 1) proximate an air valve; 2) between a fuel injection port and an ignition source; 3) downstream of both the fuel injection port and the ignition source; and 4) proximate an exit nozzle of the pulse detonation combustor. In addition, the pulse detonation combustor can have multiple plenums, for example, proximate the air valve and proximate the exit nozzle. The location and dimensions of the plenum can be selectively adjusted to control mechanical loading on the wall, the velocity of fluid flowing within the combustor, and the pressure generated by the pulse detonation combustor. | 02-21-2013 |
20130161007 | PULSE DETONATION TOOL, METHOD AND SYSTEM FOR FORMATION FRACTURING - According to one aspect of the invention, a pulse detonation tool is provided for fracturing subterranean formations. The pulse detonation tool includes a pulse detonation combustor and creates an isolated zone within a wellbore. The tool generate a series of repeating supersonic shock waves that are directed into the subterranean formation to cause propagation of multiple fractures into the formation. According to another aspect of the invention, a method and system for fracturing a subterranean formation using pulse detonation is provided. | 06-27-2013 |