| 摘要 |
1,204,734. Air turbine, compressor and fan assembly. UNITED AIRCRAFT CORP. May 13, 1968 [June 2, 1967], No.22514/68. Heading F1G. The invention relates to a compressor and turbine assembly, such as used for supplying air to an aircraft cabin, the assembly comprising a shaft rotatably mounted in a bearing assembly, a fan rotor mounted at one end of the shaft, a compressor rotor mounted at the other end of the shaft, a turbine rotor mounted on the shaft between the fan and compressor rotors, the turbine having an axial outlet adjacent the bearing assembly, the turbine outlet being so disposed that the air discharging from the turbine serves to cool the bearing assembly. In the embodiment shown, a shaft is supported in a bearing assembly 24, an axial flow fan rotor 36 being mounted at one end of the shaft, a centrifugal compressor rotor 6 being mounted at the other end of the shaft, and a radial inward flow turbine rotor 18 being mounted adjacent the compressor rotor. Bleed air is supplied from a source 2 to the inlet 4 of the compressor, the air at increased pressure and temperature passing to heat exchanger 12 where it is cooled by flow of ambient air. The cooled air then passes to turbine inlet 16 and is expanded through the turbine 18, the turbine driving the compressor 6 and the fan 36. The air discharging from the turbine at low-pressure and temperature passes to chamber 22 where it serves to cool the bearing assembly 24. The air then passes through line 28 to a point of use such as an aircraft cabin. A portion of air from the source 2 passes through line 32 under control of valve 30 to mix with the air in the space 22 thus preventing formation of ice due to the low temperature of the turbine exhaust air; alternatively air may be taken from the heat exhanger outlet 14 for this purpose. The axial flow fan 36 draws in ambient air at 34 the air passing through heat exchanger 12, through the inlet 40 to the fan and discharges through outlet 44.
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