| 摘要 |
987,625. Axial-flow compressors; gas turbine jet propulsion plant. ROLLS-ROYCE Ltd. Oct. 14, 1963. No. 40522/63. Headings F1C, F1G and F1J. In an axial-flow compressor 12 mounted within a casing 16 having a chamber 22 disposed externally thereof, the chamber communicates with the compressor by a single aperture or a single set of apertures 21 in the casing, and first and second valve devices 23, 24 communicate with the chamber and are adapted to control air flow therethrough from the chamber. The compressor 12 is the high pressure compressor of a double-spool gas turbine jet propulsion engine of the by-pass type. The valve device 23 comprises an annular valve obturating member 25 co-operating with an annular seat 26, and controls the flow of air to the engine by-pass duct 15 for anti-surge purposes. A detailed description of the valve device 23 appears in Specifications 864,519 and 938,534. The valve device 24 comprises one or more ducts 30 each containing a flap valve 31 controlling air flow to, for example, blown flaps of an aircraft or to auxiliary equipment The valve device 23 may be operated by a speed governor driven by the compressor shaft. The arrangement may be such that the flap valve 31 is closed whilst the valve device 23 is in operation. The chamber 22 may be mounted on the external casing of a simple gas turbine engine. |
