A system, as well as associated methods, for increasing the efficiency of a gas turbine including an inlet assembly and a compressor may include a housing configured to channel airstream towards the inlet assembly, an air treatment module positioned at a proximal end the housing, and at least one air conditioning module mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor. The air treatment module may include a plurality of inlet air filters and at least one blower configured to pressurize the air entering the air treatment module.

A unison ring of a gas turbine engine includes: an annular body including fiber-reinforced resin or circular-arc bodies including the fiber-reinforced resin, the fiber-reinforced resin including resin and reinforced fibers; and pin holes in which a pin is in a radial direction orthogonal to an axial direction of the unison ring. A main orientation of the reinforced fibers of the fiber-reinforced resin is directed in a circumferential direction of the unison ring.

A unison ring of a gas turbine engine includes: an annular body including fiber-reinforced resin or circular-arc bodies including the fiber-reinforced resin, the fiber-reinforced resin including resin and reinforced fibers; and pin holes in which a pin is in a radial direction orthogonal to an axial direction of the unison ring. A main orientation of the reinforced fibers of the fiber-reinforced resin is directed in a circumferential direction of the unison ring.

A vehicle includes a vehicle body, a vehicle power source, and an actuator. The vehicle power source includes a housing and a power generator. The housing is rotationally mounted on the vehicle body and is configured to rotate, relative to the vehicle body, about a first rotational axis. The power generator is rotationally mounted within the housing and is configured to rotate about a second rotational axis and generate power. The first rotational axis and the second rotational axis are orthogonally disposed. The actuator is coupled to the housing and is operable to selectively rotate the housing about the first rotational axis. By gimballing the rotating mass of the power source a gyroscopic torque can be applied to the vehicle improving its maneuverability.

A vehicle includes a vehicle body, a vehicle power source, and an actuator. The vehicle power source includes a housing and a power generator. The housing is rotationally mounted on the vehicle body and is configured to rotate, relative to the vehicle body, about a first rotational axis. The power generator is rotationally mounted within the housing and is configured to rotate about a second rotational axis and generate power. The first rotational axis and the second rotational axis are orthogonally disposed. The actuator is coupled to the housing and is operable to selectively rotate the housing about the first rotational axis. By gimballing the rotating mass of the power source a gyroscopic torque can be applied to the vehicle improving its maneuverability.

A jet engine which includes: a fan provided with a plurality of stages of rotor blades; a compressor which compresses air which is sent from the fan; a combustor which generates combustion gas by using compressed air generated by the compressor; a turbine which generates a driving force from the combustion gas; and a nozzle which discharges the combustion gas, the jet engine further includes: a variable guide vane which is disposed upstream of the rotor blades of a second and later stage of the rotor blades of the fan and which adjusts an inlet angle of air flow against the second and later stage of the rotor blades; a fluid resistance adjusting device which adjusts a fluid resistance at the nozzle; and a controller which controls the variable guide vane such that the inlet angle at the time of cruise flight is smaller than the inlet angle at the time of acceleration and controls the fluid resistance adjusting device such that increase in the fluid resistance, due to an increase in a volume flow at an outlet of the fan corresponding to a reduction in the inlet angle, is suppressed.

A jet engine which includes: a fan provided with a plurality of stages of rotor blades; a compressor which compresses air which is sent from the fan; a combustor which generates combustion gas by using compressed air generated by the compressor; a turbine which generates a driving force from the combustion gas; and a nozzle which discharges the combustion gas, the jet engine further includes: a variable guide vane which is disposed upstream of the rotor blades of a second and later stage of the rotor blades of the fan and which adjusts an inlet angle of air flow against the second and later stage of the rotor blades; a fluid resistance adjusting device which adjusts a fluid resistance at the nozzle; and a controller which controls the variable guide vane such that the inlet angle at the time of cruise flight is smaller than the inlet angle at the time of acceleration and controls the fluid resistance adjusting device such that increase in the fluid resistance, due to an increase in a volume flow at an outlet of the fan corresponding to a reduction in the inlet angle, is suppressed.

A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and coupled for rotation with the fan rotor. The at least one inducer stage is positioned upstream of the compressor section.

A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and coupled for rotation with the fan rotor. The at least one inducer stage is positioned upstream of the compressor section.

An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.