Abstract: 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.

Abstract: 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.

Abstract: A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream. The turbine system also includes a turbine for receiving the post combustion gas stream to generate a low-NOx exhaust gas stream, a heat recovery system configured to receive the low-NOx exhaust gas stream and generate a cooled air stream and an auxiliary compressor configured to generate an oxygen and water vapor deficient cooled and compressed air stream. A portion of the oxygen and water vapor deficient cooled and compressed air stream is directed to the combustor to generate an Oxygen and H2O deficient film on exposed portions of the combustor, and another portion is directed to the turbine to provide a cooling flow.

Abstract: A system includes an intercooler configured to receive an airflow from a first compressor, to transfer heat from the airflow to a working fluid, and to provide the airflow to a second compressor. The system also includes an evaporative chiller configured to receive the working fluid from the intercooler, to chill the working fluid via evaporative cooling within an ambient air environment, and to provide the working fluid to the intercooler. In addition, the system includes a desiccant system configured to reduce a humidity of ambient air within the evaporative chiller.

Abstract: In one aspect, a combustion system is configured to facilitate preventing the formation of vanadium pentoxide (V2O5) and decrease a concentration of at least one of vanadium trioxide (V2O3) and vanadium tetroxide (V2O4) particles in an exhaust. The combustion system includes a vanadium-containing fuel supply and a combustor. The combustor is configured to generate a combustor exhaust gas including vanadium trioxide (V2O3) and/or vanadium tetroxide (V2O4) particles and to combust a reduced-oxygen mixture including the vanadium-containing fuel, ambient air, and a portion of the combustor exhaust gas. The combustion system also includes a particle separator configured to remove substantially all of the V2O3 and/or V2O4 particles from the combustor exhaust gas. A method for combusting fuel and a power generation system are also provided.

Abstract: 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.

Abstract: 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.

Abstract: A method for assembling a gas turbine engine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, and coupling a low-pressure compressor between the core gas turbine engine and a motor such that the low-pressure compressor is driven only by the motor.

Abstract: A dual fuel propulsion system comprising a gas turbine engine configured to generate a propulsive thrust using a cryogenic liquid fuel.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: An engine contains at least one pulse detonation combustor having a combustion chamber and an exit nozzle coupled to and downstream of the combustion chamber. During operation of the at least one pulse detonation combustor a detonation occurs within the combustion chamber and at least one of a fuel fill fraction and purge fraction of the at least one pulse detonation combustor are utilized to offset a temperature peak of said detonation from a pressure peak of said detonation. The fuel fill fraction is defined as 1?purge fraction, and the purge fraction is the ratio of the purge time of the at least one pulse detonation combustor to a sum of the purge time of the at least one pulse detonation combustor and a fuel fill time of the at least one pulse detonation combustor.

Abstract: A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone.

Abstract: 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.

Abstract: In one embodiment, a pulse detonation engine includes a resonator configured to fluidly couple to an air flow path upstream of a pulse detonation tube. The pulse detonation engine also includes a controller configured to receive signals indicative of an operating frequency of an air valve disposed at an upstream end of the pulse detonation tube, and to adjust a geometric configuration of the resonator in response to the signals.

Abstract: 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.

Abstract: 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.

Abstract: An inlet particle separator system is provided. The system includes an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air. The system also includes a scavenge subsystem in flow communication with the axial flow separator for receiving the first flow of substantially contaminated air. Finally, the system includes a fluidic device disposed in flow communication with the first flow of substantially contaminated air for inducting air through the scavenge subsystem and the engine inlet.

Abstract: 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.

Abstract: 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.

Abstract: 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.