Compressed air supply system of aircraft
A compressed air supply system of an aircraft includes: a bleed air passage through which bleed air from a gas turbine engine flows; an auxiliary compressor including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage; a supply passage which is fluidly connected to the compressor outlet and through which compressed air from the auxiliary compressor is supplied to an air system of the aircraft; a driver that rotates the auxiliary compressor; a sensor that detects pressure or temperature of the supply passage; and circuitry that controls an output rotational frequency of the driver in accordance with a detection signal of the sensor.
1 . A compressed air supply system of an aircraft,
the compressed air supply system comprising:
a bleed air passage through which bleed air from a gas turbine engine flows;
an auxiliary compressor including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage;
a supply passage which is fluidly connected to the compressor outlet and through which compressed air from the auxiliary compressor is supplied to an air system of the aircraft;
a continuously variable transmission that rotates the auxiliary compressor by changing a speed of a driving force of a rotating shaft of the gas turbine engine and outputting the driving force to the auxiliary compressor;
a first pressure sensor that detects a pressure of the bleed air passage;
a second pressure sensor that detects a pressure of the supply passage; and
circuitry that controls an output rotational frequency of the continuously variable transmission by controlling a change gear ratio of the continuously variable transmission in accordance with a detection signal of the first pressure sensor and a detection signal of the second pressure sensor, wherein
the circuitry adjusts the pressure of the supply passage to a desired pressure by controlling the change gear ratio of the continuously variable transmission based on a pressure difference between the pressure of the bleed air passage detected by the first pressure sensor and the pressure of the supply passage detected by the second pressure sensor.
2 . The compressed air supply system according to claim 1 , wherein:
the gas turbine engine includes a low-pressure compressor and a high-pressure compressor; and
the bleed air passage is fluidly connected to at least one of a bleed air port of the low-pressure compressor of the gas turbine engine or a bleed air port of the high-pressure compressor of the gas turbine engine.
3 . The compressed air supply system according to claim 1 , further comprising:
a heat exchanger including
a target passage fluidly connected to the supply passage and
a cooling medium passage that cools the compressed air flowing through the target passage; and
an exhaust passage that connects an exhaust port of a passenger room to an inlet of the cooling medium passage, wherein
an outlet of the cooling medium passage is open to atmosphere.
4 . A compressed air supply system of an aircraft,
the compressed air supply system comprising:
a bleed air passage through which bleed air from a gas turbine engine flows;
an auxiliary compressor including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage;
a supply passage which is fluidly connected to the compressor outlet and through which compressed air from the auxiliary compressor is supplied to an air system of the aircraft;
a return passage which extends from the supply passage and through which the compressed air from the auxiliary compressor is supplied to the bleed air passage;
a pressure regulating valve that opens or closes the return passage;
a driver that rotates the auxiliary compressor;
a sensor that detects a pressure of the bleed air passage or the supply passage; and
circuitry that controls an output rotational frequency of the driver in accordance with a detection signal of the sensor, wherein
when an absolute value of a time change rate of the pressure detected by the sensor exceeds a threshold, the circuitry controls an opening degree of the pressure regulating valve such that a pressure fluctuation in the supply passage is suppressed.
5 . A compressed air supply system of an aircraft,
the compressed air supply system comprising:
a bleed air passage through which bleed air from a gas turbine engine flows;
a first auxiliary compressor including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage;
a supply passage which is fluidly connected to the compressor outlet and through which compressed air from the first auxiliary compressor is supplied to an air system of the aircraft;
a driver that rotates the first auxiliary compressor;
a second auxiliary compressor that includes a compressor inlet and a compressor outlet, is connected in parallel with the first auxiliary compressor, and is rotated by the driver, the compressor inlet being fluidly connected to the bleed air passage, the compressor outlet being fluidly connected to the supply passage;
a switching structure that switches the second auxiliary compressor between a compression state and a non-compression state;
a sensor that detects a pressure or a temperature of the supply passage; and
circuitry that controls an output rotational frequency of the driver in accordance with a detection signal of the sensor, wherein
the switching structure includes
a second return passage that bypasses the second auxiliary compressor and connects the compressor outlet of the second auxiliary compressor to the compressor inlet of the second auxiliary compressor and
a second pressure regulating valve that opens or closes the second return passage.
6 . The compressed air supply system according to claim 5 , wherein the switching structure includes a clutch that cuts a power transmitting path between the second auxiliary compressor and the driver.