A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.

A blade assembly for a gas turbine engine includes a rotor, a stator, a seal plate, and a sealing member. The rotor includes a rotor blade and a rotor disc. The rotor disc defines a bucket groove which receives a cooling fluid from a first cavity upstream of the rotor. The sealing member includes a control arm. The sealing member and the rotor define a flow cavity therebetween in fluid communication with an aperture of the seal plate. The flow cavity receives the cooling fluid flowing through the bucket groove and the aperture. The control arm and the seal plate define a gap therebetween fluidly communicating the flow cavity with a second cavity between the stator and the rotor. The control arm deflects at least a portion of the cooling fluid entering the flow cavity.

Gas turbine engines are described. The gas turbine engines include a compressor section, a combustor section, a turbine section, and a nozzle, wherein the compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle. A waste heat recovery system is operably connected to the gas turbine engine, the waste heat recovery system having a working fluid. An auxiliary cooling system is configured to provide cooling to a working fluid of the waste heat recovery system.

A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.

The present invention relates to a turbine injector comprising an annular ring extending around a longitudinal axis and having a radially outer edge and a radially inner edge. The crown has a plurality of channels for fluidly connecting the radially outer edge to the radially inner edge, each channel extending in a radial plane of the ring and having an inlet opening near the outer edge and an outlet opening near the radially inner edge, the orientation of each channel varying progressively according to a tangential component between the inlet section of the inlet opening and the outlet section of the outlet opening.

A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.

A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each having; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; and a turn joining the first leg to the second leg. A has: fiber members passing between legs of the tube sections; and an end plate.

A photonic reflector device includes a first layer, a second layer, and a third layer. The first layer, which functions as a retro-reflector, is formed of a first material contacting a second material and having a non-planar interface therebetween. The second layer, which functions as a photonic crystal, includes third and fourth materials that have different refractive indices from one another and are configured such that the second layer has a periodic optical potential along at least one dimension. The third layer, which functions as a Lambertian scatterer, includes a plurality of inclusions in a first matrix material. In combination, the layers may be optimized to synergistically reflect targeted wavelengths and/or polarizations of light.

A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.

A cryogenic oil-free direct drive turbogenerator for gas liquefaction plant applications is described. The pressure energy from cryogenic gas is expanded through a turbine and the power generated is converted into electricity through a directly driven generator and a power electronics arrangement. The machinery can withstand very cold temperature operation (e.g., <−425° F.) by isolating the cold turbine side from the warmer side of the machine turbine end and has a hermetically sealed design wherein the process gas is fully contained from leaking at operating pressures. A unique gas injection scheme uses seal gas segregation, thrust bearing cooling and pressure balance for thrust control which is accomplished through a pressure regulator arrangement. Also described is an algorithm for speed control and overspeed protection through the power electronics system. The rotating components of the turbogenerator are supported on foil gas bearings for oil-free operation eliminating extraneous lubrication.