Abstract: A method of operating a combustor of a gas turbine, the combustor including a combustor liner that defines a total combustion chamber volume, and has a primary combustion zone defining a primary volume. The combustor liner includes a movable portion that is arranged to be actuated to adjust a percentage of the primary volume with respect to the total combustion chamber volume. The method includes, at a first operating state of the gas turbine, adjusting a size of the primary volume to a first percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume, and at a second operating state of the gas turbine different from the first operating state, adjusting the size of the primary volume to a second percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

Abstract: A power plant is configured to output power to a grid power system and comprises a hydrogen generation system configured to produce hydrogen, a gas turbine combined cycle power plant comprising a gas turbine engine configured to combust hydrogen from the hydrogen generation system to generate a gas stream that can be used to rotate a turbine shaft and a heat recovery steam generator (HRSG) configured to generate steam with the gas stream of the gas turbine engine to rotate a steam turbine, a storage system configured to store hydrogen produced by the hydrogen generation system, and a controller configured to operate the hydrogen generation system with electricity from the grid power system when the grid power system has excess energy and balance active and reactive loads on the grid power system using at least one of the hydrogen generation system and the gas turbine combined cycle power plant.

Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Abstract: An assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; a locator disposed within the bearing member; a first plurality of bolts configured to attach the first end of the support bracket to the first flange; a second plurality of bolts configured to attach the second end of the support bracket to the second flange; and a mechanical fuse.

Abstract: A rotating detonation engine including an annular main chamber configured to sustain a main shockwave that moves along a perimeter of the main chamber and an annular pilot chamber configured to sustain a pilot shockwave that moves along a perimeter of the pilot chamber. The main shockwave may be generated in response to the pilot shockwave extending into the main chamber.

Abstract: An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

Abstract: A propulsion system includes multiple solid rocket motors that are activated by a single initiator. The rocket motors act in parallel, providing thrust in a single direction. The initiator activates an ignition charge that is in or operatively coupled to a non-annular plenum that transports hot gasses from the ignition charge to the rockets to be ignited. The plenum may be an unchoked plenum, allowing flow of hot gasses without choking. The plenum may be lined with an insulator material. A cover may be used to cover the plenum, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors, with propellant grains and nozzles. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge and which in turn ignite the propellant grains.

Abstract: A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.

Abstract: Power generation systems are described. The systems include a shaft, a compressor operably coupled to a first end of the shaft, a turbine operably coupled to a second end of the shaft, a generator operably coupled to the shaft between the compressor and the turbine, and a working fluid arranged in a closed-loop flow path that flows through each of the compressor and the turbine to drive rotation of the shaft. The shaft includes an internal fluid conduit configured to receive a portion of the working fluid at one of the first end and the second end and convey the portion of the working fluid through the generator to the other of the first end and the second end, wherein the portion of the working fluid is rejoined with a primary flow path of the working fluid.

Abstract: Fuel distribution manifolds and combustors are provided. A fuel distribution manifold includes a main body and a fuel circuit that is defined within the main body. The fuel circuit includes an inlet section extending generally axially from an inlet to a first branch section and a second branch section. The first branch section and the second branch section diverge circumferentially away from each other as they extend axially from the inlet section to a respective first outlet and a respective second outlet.

Abstract: Turnbuckle linkages are disclosed herein. A turnbuckle linkage includes an inside rod including a first opening on a first longitudinal end and a second opening on a second longitudinal end of the inside rod, the first opening and the second opening extending at least partially through the inside rod, the inside rod including tabs extending from the first longitudinal end and the second longitudinal end of the inside rod around the first opening and the second opening, an exterior surface of the tabs including conical threads, outside rods to be positioned within the openings of the inside rod, the tabs of the inside rod at least partially surrounding the outside rods, the outside rods including end bearings to couple to a first structure and a second structure, and conical nuts to constrict the tabs around the outside rods and couple the inside rod and the outside rods.

Abstract: A pre-swirl nozzle carrier for a gas turbine engine, includes: a wall having front and rear sides, and a multiplicity of pre-swirl nozzles formed in the wall and which each have a flow passage, wherein the flow passage has an inlet opening at the front side and an outlet opening at the rear side. The flow passages are provided and designed to discharge air, which has flowed in via the inlet opening, with swirl from the outlet opening. It is provided that the inlet opening is surrounded by a periphery which, at least in certain sections, has a region with a convex curvature adjacent to the flow passage and has a region with a concave curvature adjacent to said region with a convex curvature. The invention furthermore relates to a method for producing a pre-swirl nozzle in a pre-swirl nozzle carrier.

Abstract: Some apparatus embodiments include an aircraft having a hybrid parallel electric propulsion system including two internal combustion engines and an electric propulsion system including two electric motors electrically connected to an electric power module. The electric power module is optionally configured for attachment to a bottom side of a fuselage. Each of the electric motors attaches to an aircraft wing outboard of the nearest internal combustion engine. The electric motors and internal combustion engines are operable independently of one another, providing for propulsion by the electric motors during flight and ground operations when the internal combustion engines may operate inefficiently. Some embodiments are implemented as a hybrid parallel electric propulsion retrofit package for adding an electric propulsion system to an aircraft previously equipped only with internal combustion engines.

Abstract: An integrated combustor nozzle includes a combustion liner that extends between an inner liner segment and an outer liner segment along a radial direction. The combustion liner including a forward end portion, an aft end portion, a first side wall, and a second side wall. An impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement apertures that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel includes an inlet portion that extends from the impingement plate to a collection duct. The impingement panel further includes a plurality of supports spaced apart from one another. The plurality of supports extend between, and are coupled to, the inlet portion, the collection duct, and the impingement plate.

Abstract: An engine assembly for an aircraft including a bypass turbomachine as well as a turbomachine attachment pylon including an air-oil exchanger system arranged in an inter-ducts compartment between the flow ducts, the compartment being delimited radially on the outside by an inter-ducts cowling, the exchanger system being supplied with air from a secondary flow duct of the turbomachine delimited radially on the inside by the inter-ducts cowling, and the exchanger system being supported by a support arranged in the inter-ducts compartment, this support being mechanically connected to the attachment pylon by connecting means passing through the inter-ducts cowling.

Abstract: A gas turbine engine (1) has a centrifugal compressor (4) and a radial turbine (14) mounted to a turbine shaft (2) for rotation with the shaft about the shaft axis Z. A number of combustion chambers (10) in the air/gas flow path between the compressor and the turbine are spaced circumferentially about the shaft axis. The combustion chambers (10) are elongate in the direction of air/gas flow and the longitudinal axis of each combustion chamber is skewed transversely relative to the axis Z of the turbine shaft. The combustion chambers (10) may be curved longitudinally about the shaft axis and may be aligned concentric about the axis. The engine may have a recuperator (8) radially outboard the compressor, the recuperator having radially directed flow passages through which air from the compressor is directed.

Abstract: Various embodiments relate to combined heat and power (CHP) systems. A CHP system can include a turbine system, a turbocharger system, and a refrigeration system. The refrigeration system can receive combustion products from the turbine system and compressed air from the turbocharger system. The refrigeration system can cool the combustion products and the compressed air to generate a cooled combustion product mixture that is provided to the turbine system.

Abstract: A strut system for a RAT includes a strut body, a strut first end is connected to the aircraft and rotate about a first axis, a strut second end is spaced apart from the strut first end by the strut body and is connected to the RAT turbine generator unit, the strut has a strut conduit extending from the strut first end toward the strut second end; and a damper rod that includes a rod body and disposed within the strut conduit, the damper rod having a rod first end that is fixed within the strut conduit at the strut first end, and a rod second end that is spaced apart from the rod first end by the rod body and is located intermediate the strut first end and the strut second end, wherein the rod second end moves along a second axis that is parallel to the first axis.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section, a compressor section including a low pressure compressor and a second compressor section, and a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the low pressure compressor and the gear arrangement to drive the propulsor. A core split power ratio is provided by power input to the high pressure compressor divided by a power input to the low pressure compressor measured in horsepower.

Abstract: A method of assembling a mobile electric power generation system comprises providing a generator trailer having an electric generator, a gas turbine trailer having a gas turbine, an exhaust trailer having an exhaust device, and an air filter and ventilation trailer having an air inlet device. The method includes positioning each of the generator trailer, the gas turbine trailer, the exhaust trailer, and the air filter and ventilation trailer at a job site such that the generator trailer and the gas turbine trailer are in an end-to-end configuration. The method comprises coupling each of the generator trailer, the exhaust trailer, and the air filter and ventilation trailer to the gas turbine trailer in an operational mode for generating power and decoupling each of the generator trailer, the exhaust trailer, and the air filter and ventilation trailer from the gas turbine trailer in a transport mode for transport.