| 摘要 |
<p>1,067,110. Gas turbine plant. BENDIX CORPORATION. Feb. 25, 1966 [March 22, 1965], No. 8478/66. Addition to 1,066, 670. Heading F1G. As disclosed in the parent invention, the fuel nozzles within the combustion chamber of a gas turbine engine are supplied through three valves in series from an engine driven pump within unit 10 receiving fuel from a source at pressure P o and delivering at pressure P 1 . The pump output passes through a first valve within unit 10 positioned as a function of the setting of a speed control lever 14 and engine speed sensed by a governor. The output of the valve passes at pressure P 2 to the second valve within unit 18 positioned as a function of temperature. The output at P 3 passes to the third valve 26 controlled by atmospheric pressure and is throttled to a pressure P 4 , at which pressure the fuel is supplied to the nozzles. The system includes a by-pass valve 40 from the pump outlet to the pump inlet. In the present modification of the parent invention, valve 40 is controlled by diaphragms 32, 44, 66 acting on a lever 54 pivoted at 56 within a chamber 58. All the diaphragms are subjected on one side to atmospheric air pressure P, supplied through duct 52. The other sides of the diaphragms 32, 44, 66 are subjected respectively to the pump output pressure P 1 , the compressor discharge pressure P c and the final fuel pressure P 4 . Diaphragms 32 and 66 are of equal area and the lever arms of lever 54 on either side of pivot 56 are of equal length so that the net result is that the position of valve 40 and thus the TOTAL fuel pressure differential P 1 -P 4 across the three valves, is controlled in response to the air pressure differential P c -P a . Any air or fuel leakage past the diaphragms is vented from chamber 58 to atmosphere.</p> |
