Abstract: A gas turbine engine includes a centrifugal compressor, a combustor, a radial turbine, and a cooling air metering system. The centrifugal compressor is configured to rotate about an axis to produce compressed air. The combustor is fluidly connected downstream of the centrifugal compressor to receive the compressed air from the centrifugal compressor. The radial turbine is fluidly connected with the combustor and is axially spaced apart from the centrifugal compressor. The cooling air metering system is configured to selectively block or allow a portion of the compressed air flowing radially between the centrifugal compressor and the radial turbine, bypassing the combustor, and through a heat exchanger for cooling the radial turbine and other components.

Abstract: Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. An anti-unstart configuration provides control for transitioning between the amount of air directed to either engine during operation of gas turbine engine and scramjet engines, to avoid unstart during operation above sonic speeds.

Abstract: A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.

Abstract: A gas turbine engine includes a fan and an engine core that includes a compressor, a combustor, and a turbine. The fan and the compressor include variable pitch geometry. The gas turbine engine further includes a control system configured to adjust the variable pitch geometry of the fan and the compressor to optimize a performance characteristic of the gas turbine engine.

Abstract: A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.

Abstract: System and methods are provided that use a recharge device to resupply a reservoir and tank with fluids used to power a turbine, which in turn powers a generator, wherein one of the resupplied fluids is used to cool a load that is powered by the generator.

Abstract: A start system for an expendable gas turbine engine is provided. The start system may include: a tank configured to store a pressurized gas comprising oxygen; a non-pyrotechnic igniter in communication with a combustion chamber of the expendable gas turbine engine; a starter tube configured to feed the pressurized gas from the tank into the combustion chamber; and a valve configured to regulate a flow of the pressurized gas from the tank into the starter tube; wherein, the start system is configured to startup the expendable gas turbine engine by the flow of the pressurized gas from the tank, through the valve and the starter tube, into the combustion chamber and, from the combustion chamber, into a plurality of turbine blades of the expendable gas turbine engine, and by ignition, by the non-pyrotechnic igniter, of fuel injected into the combustion chamber.

Abstract: Systems and methods are provided that use compressed gas to power a turbine, which in turn powers a generator, where an expansion of the compressed gas provides cooling for an electrical load that is powered by the generator.

Abstract: A container may be supplied with an incompressible fluid. For example, the container may be partially or completely prefilled with the incompressible fluid. The container may be supplied with a flow of compressible gas via a first valve. The first valve may regulate the flow of the compressible gas supplied to the container based on a pressure setting of the first valve. A second valve may release the incompressible fluid from the container as the container is filled with the compressible gas and in response to a pressure of the container being greater than a pressure setting of the second valve. The pressure setting of the first valve may be greater than the pressure setting of the second valve.

Abstract: A gas turbine engine includes a lubrication system, fuel system and thermoelectric heat exchanger adapted for selective operation in response to operational states of the gas turbine engine.

Abstract: Systems and methods of augmenting the thrust of the prime power engine(s) of an aircraft from a tank of compressed gas are described herein.

Abstract: A method includes receiving, at a first device, an option to receive a video identified by a second device, the option received during a communication session between the first device and the second device. The method includes receiving, at the first device, input indicating acceptance of the offer. The method includes, in response to the input, automatically making a determination, at the first device, whether to have the video sent to a video output device that is distinct from the first device, to receive the video at the first device, or both. The determination is based on a location of the first device. The method also includes, in response to the determination indicating to have the video sent to the video output device, sending a notification to the application server. The notification identifies the video output device.

Abstract: Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. An anti-unstart configuration provides control for transitioning between the amount of air directed to either engine during operation of gas turbine engine and scramjet engines, to avoid unstart during operation above sonic speeds.

Abstract: A gas turbine engine includes a cooling air system, a coolant system, and a thermoelectric heat exchanger adapted for selective operation in response to operational states of the gas turbine engine.

Abstract: A gas turbine engine includes a compressor, a cooling source, and a thermoelectric intercooler adapted for selective operation in response to operational states of the gas turbine engine.

Abstract: Systems and methods are provided that use compressed gas from a tank in an aircraft to avoid and/or recover from a compressor surge. Systems and methods are provided that use compressed gas from a tank to startup a gas turbine engine in an aircraft, where the gas turbine engine is configured as a prime power engine for the aircraft.

Abstract: A gas turbine engine includes a fan and an engine core that includes a compressor, a combustor, and a turbine. The fan and the compressor include variable pitch geometry. The gas turbine engine further includes a control system configured to adjust the variable pitch geometry of the fan and the compressor to optimize a performance characteristic of the gas turbine engine.

Abstract: Systems and methods are provided that use compressed gas to power a turbine, which in turn powers a generator, where an expansion of the compressed gas provides cooling for an electrical load that is powered by the generator.

Abstract: A container may be supplied with an incompressible fluid. For example, the container may be partially or completely prefilled with the incompressible fluid. The container may be supplied with a flow of compressible gas via a first valve. The first valve may regulate the flow of the compressible gas supplied to the container based on a pressure setting of the first valve. A second valve may release the incompressible fluid from the container as the container is filled with the compressible gas and in response to a pressure of the container being greater than a pressure setting of the second valve. The pressure setting of the first valve may be greater than the pressure setting of the second valve.

Abstract: Systems and methods of augmenting the thrust of the prime power engine(s) of an aircraft from a tank of compressed gas are described herein.