| 摘要 |
1,210,689. Jet propulsion nozzles. GENERAL ELECTRIC CO. Dec.29, 1967 [Dec.29, 1966], No.58999/67. Heading F1J. [Also in Divisions F2 and G3] The propulsion nozzle 16 of a gas turbine engine is controlled by double-acting rams 20 supplied by spool valve 36 having pressure chambers 62, 64 at opposite ends supplied by regulating valve 68 via lines 70, 72. Valve 36 is controlled by rotary valve member 90 which controls leakage from line 72 and thus the pressure in chamber 64. Sleeve 89 rotates in response to spool movement to provide a feedback. Valve member 90 is rotated by axial movement of piston 96 via links 94, 92, the piston 96 being controlled by jet-pipe servovalve 122 in response to gas temperature signals transmitted electrically by amplifier 164. Feedback signals are transmitted at 106 to rotary cam 102 to cause the latter to adjust the pivot point 98 of link 94. Piston 96 is movable between limits set by pilot's lever 184, the range of movement increasing with increased engine operation as dictated by the position of lever 184. As shown, the limits are defined by stops 188 carried by levers 162, 164 positioned by rotary cams 180, 182. The stops 188 co-operate with flappers 190, 192 carried by piston 96 and controlling bleed tubers 194, 195 through the end walls of the piston. The latter will thus move in response to movement of jet-tube 124 until a flapper is unseated by contacting a stop to cause a pressure balance across the piston. The chamber 136 of valve 122 is maintained pressurized, by valve 138, and a constant pressure differential is maintained across spool 36 by by-pass valve 50 which senses the higher of the pressures in lines 26, 28 via selector valve 55. The velocity of piston 96 is proportional to the temperature error signal, and valve 68 compensates for variations in fuel viscosity. |
