| 摘要 |
1,256,122. Axial-flow compressors; jet propulsion plant. GENERAL ELECTRIC CO. March 4, 1969 [March 6, 1968], No. 11449/69. Headings F1C, F1J and F1T. A compressor, e.g. in a turbofan engine as shown, comprises a rotor 34 having a row 36 of relatively long blades extending to an outer duct wall 38, and a row 62 of relatively short blades extending to a splitter ring 54. Air discharged at relatively low energy from the inner portion of blade row 36 is guided by vanes 56 into the blade row 62 where it received additional energy. Air discharged at relatively high energy from the remaining portion of the blade row 36 passes through flow straightening vanes 70, struts 72 and a propulsion nozzle 15. Flow straightening vanes 64 are inclined as shown in Fig. 3 with their concave surfaces facing generally towards the inner wall 80, to encourage the air to flow inwardly into inlet 46 of high-pressure compresser rotor 24. The leading edge of nacelle 42 forms a second splitter. During deceleration of the engine, the rotor 24 decelerates more rapidly than the rotor 34 and therefore is incapable of receiving all of the air leaving the vanes 64. However, the excess is readily diverted into nozzle 15 without substantial increase in back pressure and consequent stall at the vanes 64. |
