发明名称 AIRCRAFT ENGINE FUEL SYSTEM
摘要 <p>1332072 Aircraft fuel systems; centrifugal pumps GENERAL ELECTRIC CO 12 Jan 1971 [20 April 1970] 1433/71 Headings F1C and F1G The invention relates to an aircraft engine fuel system which is adapted to provide a quantity of pressurized fuel for operating the pumping system of an aircraft fuel transfer system. The aircraft shown comprises two engines 12, 14, two wing-mounted fuel tanks 16, 18 and a fuselage-mounted fuel tank 20. Fuel is supplied to the engine fuel systems 26, 28 from the tank 20 by means of jet type transfer pumps 36, 40 through lines 22, 24. Fuel is transferred from the wing tanks 16, 18 to the fuselage tank 20 by means of jet type transfer pumps 34, 38 through lines 30, 32. The jet type transfer pumps are supplied with a fuel from the engine fuel pumps such as 50, Fig.2, as the motive fluid. The fuel pump 50 is part of the fuel system 26 of the engine 12 and is a centrifugal type pump comprising an impeller 74 driven by shaft 76, the pump receiving fuel from tank 20 and jet type pump 36 through line 22. The casing of the pump is formed with an outlet 84 adjacent the periphery of the impeller through which clean fuel is passed through line 86 to pump 88 where it is pressurized and passed through lines 42, 44 to act as motive fluid for the jet type pumps 34, 36. The remaining portion of fuel from the impeller which may contain centrifuged impurities, passes through diffuser outlet 82 and passes to fuel heater 52, filter 54, engine fuel pump 56, fuel control 58, thence through line 60 to the engine combustion equipment 62. Excess fuel may pass from the control 58 through line 64 back to the inlet of the fuel heater 52. Compressor discharge air is tapped from the engine 12 and passed through line 66 to the fuel heater 52. In prior systems fuel has been taken from the discharge side of the fuel pump 56 through line 70 as indicated to constitute motive fluid for the jet type fuel transfer pumps. In the fuel system according to the invention the fuel constituting the jet type pump motive fluid does not pass through the heater 52.</p>
申请公布号 CA918936(A) 申请公布日期 1973.01.16
申请号 CA19710104948 申请日期 1971.02.10
申请人 GEC 发明人 HULL T N
分类号 B64D37/14 主分类号 B64D37/14
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