A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.

A fuel delivery system for a gas turbine engine comprises a cryogenic fuel tank, a first fuel line for connection to the cryogenic fuel tank, a fuel pump connected to receive fuel via the first fuel line, a plurality of fuel lines connecting the fuel pump to a combustor of the gas turbine engine, a controller configured to operate the fuel delivery system, a purge gas tank connected to the first fuel line and configured to store a purge gas for purging the plurality of fuel lines and a fuel gas tank connected to the first fuel line and configured to store a fuel gas for flushing purge gas from the plurality of fuel lines.

An exhaust system includes an exhaust manifold structured to be fluidly coupled to an engine. A turbocharger including a turbine housing is fluidly coupled to the exhaust manifold. An exhaust pulse converter includes a first portion integral to the exhaust manifold and a second portion integral to the turbine housing. The exhaust pulse converter is structured to reduce engine pumping losses by reducing cross-talk of exhaust blowdown events from the engine.

A circuit (10) for draining at least one combustible fluid for a cavity of a turbine includes a drain (12) in fluidic communication with the at least one cavity, and a first isolation valve (14) and a second isolation valve (16) defining between them an isolation cavity (C) of a portion of the drain. A discharge line (18) is in fluidic communication with the isolation cavity (C) to allow the discharge of air out of the isolation cavity (C). A supply line (22) supplies pressurized fluid to the isolation cavity (C), and a supply valve (24) is arranged in the supply line (22) for regulating the supply of the isolation cavity (C) with pressurized fluid. A discharge valve (20) is arranged in the discharge line (18) for regulating the discharge of the gases out of the isolation cavity (C), and—a device (26) is provided for determining a failure of the drainage circuit (10).

Embodiments of systems and methods for air recovery are disclosed. The diverted pressurized air may be used to supply a hydrostatic purge to the unutilized portion of a turbine engine fuel manifold circuit to ensure that exhaust gases from the utilized side of the fuel manifold circuit do not enter the portion of the alternative fuel manifold circuit rack. The assembly used to remove compressor section pressurized air may include a flow control orifice, line pressure measuring instrumentation, non-return valves, isolation valves and hard stainless-steel tubing assemblies. In some embodiments, a turbine compressor section diverter system may include a small air receiver used to increase the volume of air supplying the manifold to aid in potential pressure and flow disruptions from a turbine engine compressor section.

An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.

A de-aerator for a lubrication system, has: a housing defining an air-oil inlet, an oil outlet, and an air outlet of the de-aerator; a rotor received within the housing and rotatable relative to the housing about a central axis, the rotor having blades distributed about the central axis and extending at least partially radially relative to the central axis, flow passages extending between the blades, the rotor having a hub circumferentially extending around the central axis and around the blades, the hub having a peripheral wall oriented radially inwardly and defining a fore opening leading to the flow passages; and a gap between the housing and the hub of the rotor, a portion of the housing received within the fore opening and axially overlapping the peripheral wall of the hub, the gap having a fore gap inlet between the portion of the housing and the peripheral wall of the hub.

A gas turbine engine includes a power unit and an oil system configured to lubricate the power unit during operation of the gas turbine engine. The power unit includes an engine core and a fan coupled with the engine core and driven by the engine core to produce thrust for propelling the gas turbine engine during operation of the gas turbine engine.

An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

A diffuser and deswirl flow structure includes a plurality of tube structures with an outer wall that is hollow and elongate and that extends between a first portion and a second portion. The plurality of tube structures is disposed in an annular arrangement about the longitudinal axis. The flow structure also includes a plurality of flow passages extending through the tube structures. The plurality of flow passages extend from the first portion to the second portion, respectively. The plurality of flow passages respectfully include a diffuser portion, which is proximate the first portion and configured to diffuse a fluid flow from a compressor wheel. The plurality of flow passages respectfully include a deswirl portion, which is proximate the second portion and configured to deswirl the fluid flow from the diffuser portion. The outer wall defines the diffuser portion and the deswirl portion. The outer wall is self-supporting.