| 摘要 |
<p>1,104,887. Refrigerating. WESTLAND AIRCRAFT Ltd. 18 Jan., 1966 [22 Jan., 1965], No. 3025/65. Heading F4H. In an air cooling system 1 for a supersonic aircraft having a cabin with inner and outer walls 2 and 3, the air from the cabin is discharged via a duct 26 through an expansion turbine 28 and forms the cooling medium in a heat exchanger 29, and discharges through a nozzle 30 to ambient 25, the turbine 28 driving a fan 31 which circulates the air to be cooled in the heat exchanger 29 through ducts 32 and 33 and around the inter-wall space 4. A shut-off valve 27, which can be manually or automatically controlled in association with a cabin discharge valve 23, is provided. In a modification (Fig. 2), the turbine 28 drives a compressor (34) downstream of the heat exchanger 29 to give added thrust from the nozzle 30; a particular form of shut-off valve incorporating an absolute capsule (50) is. also described. The temperature of the supply of compressed air for the cabin, which is bled from the engine 6 via heat exchanger 7, compressor 8, heat exchangers 9 and 10, expansion turbine 15 and duct 16 is regulated by a valve 18 in by-pass channel 17, the valve being controlled by temperature selector 19, temperature sensors 20 and 21 and temperature control gear 22. An example with relative values of thrust, pressure, temperature, etc. is described. A fluid medium other than air may be sealed in the space 4. Also, the lagging may be a honeycomb arrangement or a plurality of skins. Radial flow turbines and compressors may be used, surplus power from turbine 28 may be used to drive an auxiliary electric generator.</p> |
