Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.

Abstract: A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.

Abstract: The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOx emissions.

Abstract: A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.

Abstract: A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel including methane. The assembly also includes a fuel reformer configured to produce a secondary fuel, wherein the fuel reformer is further configured to channel a flow of secondary fuel towards the rotating detonation combustor such that the fuel-air mixture further includes the secondary fuel.

Abstract: A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly also includes a first compressor configured to discharge a flow of cooling air towards the rotating detonation combustor, and to channel the flow of cooling air through the cooling conduit.

Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.

Abstract: The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOx emissions.

Abstract: 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.

Abstract: A power generation system and method of generating power with reduced NOx emission includes a gas turbine system. The turbine system includes a compressor configured to receive a feed oxidant stream and supply a compressed oxidant stream to a combustion chamber and an expander configured to receive a discharge stream from the combustion chamber and generate an exhaust stream comprising carbon dioxide and electrical energy. The system further includes an exhaust gas recirculation system configured to generate a recycle stream, wherein the recycle stream is mixed with a fresh oxidant to generate the feed oxidant stream. The exhaust gas recirculation system includes an exhaust gas recirculation control loop to control a pilot ratio (diffusion to total fuel ratio) based on received feedback related to combustion parameters. The control loop configured to control the pilot ratio required to keep NOx in its minimum ratios with improved flame stability.

Abstract: 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.

Abstract: A detonation device cleaning system includes a vessel having a main body including an outer surface and an inner surface that collectively define an interior chamber. A detonation combustor cleaning device is mounted to the vessel. The detonation combustor cleaning device includes at least one combustion chamber that defines a combustion flow path. The at least one combustion chamber includes a deflection member arranged along the combustion flow path. An ignition device is operatively connected to the at least one combustion chamber. The ignition device is selectively activated to ignite fuel within the at least one combustion chamber to produce a shockwave that moves in a first direction along the combustion flow path, is redirected back along the flow path within the at least one combustion chamber, and passes into the interior chamber to dislodge particles clinging to the inner surface of the vessel.

Abstract: A detonation device cleaning system includes a vessel having a main body including an outer surface and an inner surface that collectively define an interior chamber. A detonation combustor cleaning device is mounted to the vessel. The detonation combustor cleaning device includes at least one combustion chamber that defines a combustion flow path. The at least one combustion chamber includes a deflection member arranged along the combustion flow path. An ignition device is operatively connected to the at least one combustion chamber. The ignition device is selectively activated to ignite fuel within the at least one combustion chamber to produce a shockwave that moves in a first direction along the combustion flow path, is redirected back along the flow path within the at least one combustion chamber, and passes into the interior chamber to dislodge particles clinging to the inner surface of the vessel.

Abstract: A detonation combustor cleaning device includes at least one combustion chamber having combustion flow path and including a deflection member. An ignition device is operatively connected to the at least one combustion chamber is selectively activated to ignite a combustible fuel within the at least one combustion chamber to produce a shockwave that moves in a first direction along the combustion flow path, impacts the deflection member, reverses direction and passes into a vessel to dislodge particles clinging to inner surfaces thereof.

Abstract: A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the chamber to facilitate controlling air flow into the chamber. The device also includes a body portion extending downstream from and circumferentially around the inlet, wherein the body portion is positioned in flow communication with the inlet.

Abstract: A pulsed detonation combustor (PDC) is described. The PDC includes an outer casing defining a first hollow chamber configured to receive a flow and an inner liner. The inner liner includes at least one portion positioned within the first hollow chamber and configured to receive the flow from a plenum formed between the outer casing and inner liner. The PDC further includes a flow turning device with geometric features configured to direct the flow from the plenum to a second hollow chamber defined within the inner liner. The PDC also includes at least one fuel injection port located downstream of an inlet to the outer casing and an ignition device located downstream of the at least one fuel injection port and configured to periodically ignite fuel.

Abstract: Embodiments provide systems and methods for removing debris from a surface. A system can include a first impulse cleaning device and a second impulse cleaning device, each impulse cleaning device generating shock waves directed to a surface to be cleaned, wherein the first impulse cleaning device and the second impulse cleaning device are oriented such that the respective shock waves intersect at or proximate the surface. The system can further include a controller in operable communication with the first impulse cleaning device and the second impulse cleaning device, wherein the controller is configured to selectively cause phased operation of the first impulse cleaning device and the second impulse cleaning device such that the phased operation selectively controls the location of the intersection of the respective shock waves.

Abstract: A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor device operates in a steady, constant pressure deflagration mode, receiving its fuel from the fuel injector. In a second mode of operation the dual mode combustor device operates in a pulse detonation mode, receiving its fuel from the high frequency solenoid valve.

Abstract: A pulse detonation engine contains a mechanically driven timing device coupled with a stator device, where the timing device has both an opening portion and a blocking portion. The opening and blocking portions open and close air flow access to a detonation chamber of the pulse detonation engine at appropriate times during the pulse detonation cycle.

Abstract: An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.