Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.

Abstract: A combustor including a skeleton structure. The combustor further includes at least one liner operably coupled to the skeleton structure to at least partially define a combustion chamber, and a plurality of first planks mounted to a first side of the at least one liner and a plurality of second planks mounted to a second side of the at least one liner. The combustor also includes at least one dilution hole structure provided with a portion of the skeleton structure, and including at least one dilution hole configured to allow fluid to pass therethrough into the combustion chamber.

Abstract: A combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, a plurality of hot side planks mounted to a hot side of the inner mesh structure, and a plurality of cold side planks mounted to a cold side of the inner mesh structure. The outer liner includes an outer mesh structure, a plurality of hot side planks mounted to a hot side of the outer mesh structure, and a plurality of cold side planks mounted to a cold side of the outer mesh structure. The combustor further includes a plurality of clips configured to couple the plurality of hot side planks and the plurality of cold side planks to a plurality of structural elements of the inner mesh structure and the outer mesh structure.

Abstract: A fuel delivery system for a gas turbine engine includes a fuel tank; a draw pump downstream of the fuel tank for generating a liquid fuel flow from the fuel tank; a main fuel pump downstream of the draw pump; and a fuel oxygen conversion unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen conversion unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture; and a dual separator pump in fluid communication with the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture into a stripping gas flow and the liquid fuel flow at a location upstream of the main fuel pump.

Abstract: A rocket engine system including a coolant source containing a coolant fuel. The coolant source for providing the coolant fuel to a first surface of a wall partially defining a combustion chamber of a rocket engine, and the coolant fuel provides film cooling of the first surface of the wall. An oxidizer source for providing an oxidizer to a second surface of the wall. A monitor configured to control flow of the coolant fuel and the oxidizer, and to ensure that a stoichiometry of a combination of the coolant fuel and the oxidizer, after the coolant fuel has completed the film cooling of the first surface of the wall, is appropriate for generating a combustion of the combination of the coolant fuel and the oxidizer.

Abstract: A combustor for a gas turbine engine includes a forward liner segment having an aft end portion. The forward liner segment at least partially defines a primary combustion chamber. The combustor further includes an aft liner segment having a forward end portion. A channel is defined between the forward liner segment and the aft liner segment. The channel directs a stream of dilution air in a counter-flow or reverse direction with respect to combustion gases flowing from the primary combustion chamber during operation of the combustor.

Abstract: A combustor includes a combustor liner defining a combustion chamber and a fuel and air mixing body connected to the combustor liner to deliver mixed fuel and air into the combustion chamber. The mixing body includes an inner housing member centered on a center axis and an intermediate housing member. A mixing passage is defined between the inner and intermediate housing members. The mixing passage extends along a direction from an upstream end to a downstream end with a circumferential component, a component in an axially downstream direction, and a radially inward component with at least one air inlet into the mixing passage. A fuel supply extends into the mixing passage at a location downstream of the air inlet. The mixing passage extends downstream to supply fuel and air into the combustion chamber. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.

Abstract: An engine system includes an engine duct and a tail cone arranged radially inwardly of the engine duct. The tail cone has an outer surface and an inner surface. A generator housing is arranged in the tail cone. The generator housing includes an outer surface portion spaced from the inner surface of the tail cone. A generator is mounted in the generator housing. An air duct extends from the generator, through the generator housing, through the tail cone, and through the engine duct. The air duct includes an opening exposed to an air stream passing over the engine duct.

Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.

Abstract: A gas turbine engine according to an example of the present disclosure may include, among other things, a fan section including a fan having a plurality of fan blades and including an outer housing surrounding the fan blades to establish a bypass duct, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a fan drive turbine, the fan drive turbine driving the fan through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.

Abstract: Providing mobile electric power comprising a power generation transport configured to convert hydrocarbon fuel to electricity and an inlet and exhaust transport configured to: couple to at least one side of the power generation transport such that the inlet and exhaust transport is not connected to a top side of the power generation transport, provide ventilation air and combustion air to the power generation transport, collect exhaust air from the power generation transport, and filter the exhaust air.

Abstract: A combustor for a gas turbine includes a dome, and a deflector connected to the dome to define a baffle cavity therebetween, the deflector having a deflector cold side adjacent to the baffle cavity and a deflector hot side adjacent to a combustion chamber. At least one dome-deflector connecting member connects the dome and the deflector to each other. The dome-deflector connecting member forms a flexible joint between the dome and the deflector.

Abstract: A fuel system for a gas turbine engine includes a main fuel pump generating a main fuel flow into a main fuel passage and a secondary pump generating a secondary fuel flow into a secondary flow passage. A first control valve is disposed in a passage between the main fuel passage and the secondary flow passage. The first control valve selectively directs an excess portion of the main fuel flow to the secondary flow passage to provide at least a portion of the secondary fuel flow.

Abstract: A noise attenuation panel for a structure within a propulsion system includes a first plurality of unit cells; and a second plurality of unit cells, the second plurality of unit cells merged within the first plurality of unit cells, the first plurality of unit cells including a first periodic structure having a first unit cell, a second unit cell, a third unit cell and a fourth unit cell, each of the first unit cell, the second unit cell, the third unit cell and the fourth unit cell including a central body interconnected via a plurality of lateral tubes extending from the central body, the first periodic structure forming a first lateral layer of unit cells.

Abstract: Turbine engine systems and aircraft having such systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a drive shaft having at least a compressor section and a turbine section coupled thereto, a cryogenic fuel tank configured to supply a fuel to the combustor, and an expansion turbine mechanically coupled to the drive shaft, the expansion turbine configured to receive fuel from the cryogenic fuel tank and expand said fuel, wherein expansion of said fuel by the expansion turbine drives rotation of the expansion turbine to provide power input to the drive shaft.

Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).

Abstract: A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger and expanded through a power turbine that is coupled to drive the auxiliary compressor section.

Abstract: There are describes methods and systems for operating an engine coupled to a fuel system having a fuel manifold configured to supply fuel to a combustor of the engine. The method comprises receiving a gaseous fuel flow request indicative of a change in demand for gaseous fuel to the engine; applying a fuel loss bias to the gaseous fuel flow request to obtain a biased fuel flow request, the fuel loss bias associated with a change in mass flow rate of the gaseous fuel from the fuel manifold to the combustor in response to the change in demand; and causing the gaseous fuel to flow into the combustor in accordance with the biased fuel flow request.

Abstract: A dome structure for a combustor of a gas turbine includes a frame structure extending circumferentially about a combustor centerline axis, and a plurality of integrated dome-deflector plate members mounted to the frame structure. Each of the plurality of integrated dome-deflector plate members includes a dome wall, a deflector wall, and a plurality of side walls connecting the dome wall and the deflector wall to each other. A cavity is defined by the dome wall, the deflector wall, and the plurality of side walls.