Abstract: In a first embodiment, a system, including an exhaust duct configured to flow an exhaust gas, and an air injection system coupled to the exhaust duct, wherein the air injection system comprises a first air injector configured to inject air into the exhaust duct to assist flow of the exhaust gas through the exhaust duct.

Abstract: A blade is formed with blade air passages connecting the inside of a blade body of the blade and the inside of a platform of the blade. The platform is formed with pressure side passages that extend from the blade air passages toward a circumferential pressure side, are open at a pressure side end face, and are arranged in an axial direction. Further, the platform is formed with a suction side main passage into which cooling air flows, and a suction side passage that communicates with the suction side main passage and extends from the suction side main passage along a suction side end face.

Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.

Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.

Abstract: A fuel injector assembly includes a fuel injector and a fuel injector shroud housing the fuel injector. The fuel injector includes a body and a nozzle coupled to the body. The fuel injector shroud includes a swirler device defining a center opening proximate to the nozzle of the fuel injector and a plurality of swirler holes surrounding the center opening, a body section with an air inlet configured to admit a flow of air into the fuel injector shroud and a dome section defining a mount for securing the swirler device to the body section, and at least one interior rib positioned on an interior surface of the dome section configured to direct the flow of air to the swirler holes of the swirler device such that the flow of air exiting through the swirler is mixed with the flow of fuel exiting the nozzle.

Abstract: A turbomachine component includes a body having an exterior surface and an interior surface, an internal cavity defined by the interior surface, and a reactivity neutralizing member arranged within the internal cavity. The reactivity neutralizing member is configured and disposed to neutralize turbomachine combustion products on the interior surface of the body.

Abstract: A gas engine assembly includes a compressor, a combustion system, a bypass line and a control system. The control system is configured to control gas supply parameters based on a transportation delay value. The transportation delay value corresponds to a delay between a time when a gas supply control mechanism is adjusted and a time that gas having a corresponding adjustment of a gas characteristic is received at a predetermined point downstream from the gas supply control mechanism.

Abstract: The chamber (4) of the turbine engine (1) comprises a continuous detonation wave engine (6) provided with an annular detonation chamber (7) and associated means (8, 9) that can be used to generate a continuous production of hot gases from a detonation mixture of fuel and air. The continuous detonation wave engine (6) is arranged such as to form, from a flow of incoming air (E), a first flow (F1) which enters the detonation chamber (7) and which is used by the engine (6) and a second flow (F2) which bypasses the chamber. The turbine engine (1) also includes auxiliary means (10) for mixing the hot gases (F3) leaving the detonation chamber (7) with the second flow of air (F2) before directing same towards the turbine (5). A plurality of detonation chambers (7) are arranged concentrically to one another relative to the axis of the turbine engine.

Abstract: A turbofan engine control system for managing a low pressure turbine speed is provided. The turbofan engine control system includes a low spool having a low pressure turbine that are housed in a core nacelle. The low pressure turbine is adapted to rotate at a speed and includes a maximum design speed. A turbofan is coupled to the low spool. A fan nacelle surrounds the turbofan and core nacelle and provides a bypass flow path. The bypass flow path includes a nozzle exit area. A controller is programmed to command a flow control device adapted to effectively decrease the nozzle exit area in response to a condition. Reducing the nozzle exit area, either physically or otherwise, maintains the speed below the maximum design speed.

Abstract: Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection, the projection comprising a first surface and a second surface formed on the projection and configured to engage the inner surfaces, the first and second surfaces generally perpendicular to radial.

Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define an angled first inner surface of the first end piece. The root portion defines a first projection adapted to project into a recess portion of the attachment slot. A second end piece fits between the first inner surface and a sidewall portion of the attachment slot and includes a platform portion and a root portion that define a second projection adapted to project into a recess portion of the attachment slot. The platform portion and the root portion define an angled second inner surface and that is configured to mate with the first inner surface. A borehole extends through the platform portion of the first end piece and the root portion of the second end piece and a fastener extends through the borehole.

Abstract: A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine.

Abstract: The present invention is a prime mover with recovered energy driven compression for stationary and motor vehicle application. Efficient low compression operation, especially beneficial to small gas turbines, is enabled with either ambient or cryogenic intake air. Recovered energy, liquefied air cooling and re-liquefaction of air by a cryogenic sink minimize motive fluid compression work of a jet compressor driving exhaust gas recirculation. Regenerative heat exchanger terminal temperature difference relative to turbine temperature drop and heat exchanger surface area are reduced.

Abstract: The present invention relates to an automatic method of regulating a power plant (3?) of an aircraft (1), the power plant having at least one turbine engine (3), each engine (3) being capable of operating in an idling mode of operation. A calculation system (15) executes stored instructions in order to implement the idling mode of operation as a function of operational and ordered conditions either via a first regulation mode by regulating a first speed of rotation (Ng) of said gas generator (4), or via a second mode of regulation by regulating a second speed of rotation (NTL) of said free turbine (7).

Abstract: A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.

Abstract: A power supply device or system for aeronautics, having a hydrocarbon supply for supplying an engine with hydrocarbon fuel and a hydrogen supply having a fuel reformer for producing hydrogen from hydrocarbon fuel from said hydrocarbon supply. The hydrogen supply is connected to a hydrogen-powered fuel cell for producing electric power and to a hydrogen injecting system for injection of hydrogen into a combustion chamber of the engine. Further, the invention relates to an aircraft having an engine that can be supplied by that power supplying device or system, and to a method for operating said engine.

Abstract: The invention relates to a control system for at least one actuator (6) for the cowlings of a thrust inverter in a turbojet engine, that comprises an assembly of actuation and/or control components. A control means (9) is provided for detecting the failure of an actuation and/or control component (7, 16, 13), for determining the blocking or non-blocking character of the failure for the system operation and, in case of a non-blocking failure, for switching from a nominal operation mode to a failure-adaptation operation mode in which the failure of the actuation and/or control component (7, 16, 13) is compensated at least partially by a modified instruction of the other actuation and/or control components (7, 16, 13).

Abstract: A combustion system premixer includes one or more streamwise vortex generators configured to passively redirect surrounding high velocity air into at least one of wake and vortex regions within a combustion system fuel nozzle in response to air passing through the premixer. The streamwise vortex generators operate to minimize turbulent flow structures, thus improving air/fuel mixing, and enhancing resistance to flame-holding and flash-back within the premixer.

Abstract: A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a transpiration member. The transpiration member is at least partially surrounded by a pressure containment member. The combustion chamber has opposed inlet and outlet portions. The inlet portion of the combustion chamber is configured to receive the fuel mixture for the fuel mixture to be combusted at a combustion temperature. The combustion chamber is further configured to direct the resulting combustion product toward the outlet portion. The transpiration member directs a transpiration substance therethrough toward the combustion chamber for buffering interaction between the combustion product and the transpiration member. Associated systems, apparatuses, and methods are also provided.

Abstract: The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel injection system positioned within the head end plenum and upstream of the premixer. The injection system may be configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel. The injection system also may be configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. The present application and the resultant patent also provide a related method of operating a dual fuel combustor.