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首页> 外国专利> NECESSARY PRESSURE AND FUEL CONSUMPTION IN THE AIRCRAFT GAS TURBINE ENGINE FUEL SYSTEM DEVELOPMENT METHOD

NECESSARY PRESSURE AND FUEL CONSUMPTION IN THE AIRCRAFT GAS TURBINE ENGINE FUEL SYSTEM DEVELOPMENT METHOD

机译：飞机燃气轮机发动机燃油系统开发中的必要压力和燃油消耗

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FIELD: engines and pumps.;SUBSTANCE: invention relates to the necessary pressure and fuel consumption in the aircraft gas turbine engine fuel system development method. Pressure and fuel consumption development method in the aircraft gas turbine engine fuel system containing the electrically driven fuel pump, mechanically driven from the drives box fuel pump, fuel meter / distributor, controller, sensors, consisting in the fact, that enabling the fuel system and the gas turbine engine operation by supplying fuel from the electrically driven pump for up to 40 % of the gas turbine engine maximum rotor speed, gradually reducing the electric driven fuel pump rotation speed, and / or opening the fuel bypass from the electric driven pump outlet to the fuel system input, at the gas turbine engine rotor rotation speeds of more than 40 % enabling the necessary fuel consumption by supply from the mechanical driven fuel pump and from the electric driven fuel pump, at the electric driven fuel pump operation stages in the fuel system, in addition to the required fuel consumption in the combustion chamber, they additionally enabling the necessary pressure and fuel consumption for the hydraulic actuating units and fuel distribution units operation, after the gas turbine engine start-up completion and when the gas-turbine engine reaches the idle power mode, the electrically driven pump is transferred to the stand-by mode with reduced head on or switched off, ground idle power mode and all engine modes with the gas turbine engine rotor and the power-driven fuel pump drive shaft speeds of more than in the idle power mode are enabled by the power-driven fuel pump operation to supply the required fuel consumption into the gas turbine engine combustion chamber and develop the necessary fuel consumption and pressure for the hydraulic actuators operation, in addition, in the gas turbine engine operating modes with the gas turbine engine rotor speeds above 40 % and the occurrence of conditions with insufficient fuel pressure at the mechanical driven fuel pump inlet or outlet, as well as fuel temperature below +10 °C at the mechanical driven pump inlet turning on and / or increasing the rotor speed for the electrically driven fuel pump and maintaining the fuel pressure or temperature at the required level.;EFFECT: present invention allows to eliminate restrictions on the fuel flow and pressure at the gas turbine engine low rotation speed, reduce the fuel pre-heating amount from the fuel pump with unregulated performance (mechanical drive) in the gas turbine engine main modes with low fuel consumption, increase the gas turbine engine fault tolerance in terms of the “spontaneous shutdown” functional failure, enable conditions for the fuel pumps long-term life achievement, to obtain the fuel pumps optimal weight and size parameters.;1 cl, 1 dwg
机译：技术领域本发明涉及飞机燃气涡轮发动机燃料系统开发方法中必要的压力和燃料消耗。飞机燃气涡轮发动机燃油系统中压力和燃油消耗的开发方法，其中包括电驱动的燃油泵，由驱动箱燃油泵，燃油表/分配器，控制器，传感器机械地驱动，从而使燃油系统和通过从电动泵提供的燃料最多达到燃气涡轮发动机最大转子转速的40％，逐步降低电动燃料泵的转速和/或从电动泵出口打开燃油旁通管来实现燃气涡轮发动机的运行在燃气涡轮发动机转子转速超过40％的情况下，通过从机械驱动的燃油泵和电动驱动的燃油泵供油，在燃油驱动系统的电动运行阶段，达到了所需的燃油消耗燃油系统，除了燃烧室所需的燃油消耗外，还可以实现必要的压力和燃油在燃气涡轮发动机启动完成后以及当燃气涡轮发动机达到怠速功率模式时，液压致动单元和燃料分配单元的运行消耗，电动泵将以减少的水头行驶转换为待机模式或关闭时，地面空转功率模式和所有具有燃气涡轮发动机转子且功率驱动的燃料泵驱动轴转速大于空转功率模式的发动机模式都可以通过功率驱动的燃料泵运行来提供所需的功率进入燃气涡轮发动机燃烧室的燃料消耗，并为液压执行器的运行开发必要的燃料消耗和压力，此外，在燃气涡轮发动机转子速度高于40％且发生条件不足的燃气涡轮发动机运行模式中机械驱动燃油泵进口或出口处的燃油压力，以及机械驱动燃油泵进口tur的燃油温度低于+10°C启用和/或增加电动燃油泵的转子转速，并将燃油压力或温度保持在所需水平。效果：本发明可以消除对燃气涡轮发动机低转速时燃油流量和压力的限制，以低油耗的燃气轮机主模式减少性能不佳（机械驱动）的燃油泵的燃油预热量，就“自发停机”功能故障而言提高燃气轮机的容错能力，使燃油泵的长期使用寿命的条件，以获得燃油泵的最佳重量和尺寸参数。; 1 cl，1 dwg

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