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公开(公告)号：US4606191A
公开(公告)日：1986-08-19
申请号：US755434
申请日：1985-07-16
CPC分类号： F02C9/36 , F02C9/28 , F05D2270/101
摘要： A fuel control unit forms part of a control system of a gas turbine aeroengine. The control unit is in communication with a main fuel line leading to the aeroengine and comprises a fuel accumulator, i.e. volume varied by free piston, which is controllable by the control system to take fuel from the fuel line to reduce temporarily but substantially the mass flow of fuel to the aeroengine. This is helpful in combating surge conditions in the aeroengine caused by temporary overfueling of the aeroengine by the fuel control system.
摘要翻译： 燃料控制单元构成燃气轮机航空发动机的控制系统的一部分。 控制单元与通向航空发动机的主燃料管线连通，并且包括燃料蓄积器，即，由自由活塞变化的容积，其由控制系统控制以从燃料管线中获取燃料以暂时减少但基本上质量流量 的燃料到航空发动机。 这有助于消除燃料控制系统由航空发动机暂时过度燃油引起的航空发动机的喘振条件。
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2.发明授权
公开(公告)号：US5177951A
公开(公告)日：1993-01-12
申请号：US863036
申请日：1992-04-03
申请人： Reginald J. Butler
发明人： Reginald J. Butler
CPC分类号： F02C7/14 , F02C7/232 , Y02T50/675
摘要： A program-controlled heat management system for an aircraft's bypass gas turbine (turbofan) engine installation, in which the engine's fuel system is put into direct heat exchange relationship with the engine's own oil system, and with an engine-driven electrical generator's oil system, by means of respective fuel/oil heat exchangers and also into selective indirect heat exchange relationship with a variable proportion of the engine's bypass air means of an engine oil/air heat exchanger. The fuel system is switchable between four different fuel flow configurations in order to vary the heat flows between the fuel system and the oil systems, two of the fuel flow configurations also involving recirculation of fuel from the engine's fuel system to a fuel tank in the aircraft wing in order to put the fuel system into selective heat exchange relationship with the tank and hence with the airstream passing over the wing. Temperatures in the oil and fuel systems are monitored and kept within predetermined limits by selecting the appropriate fuel flow configuration and selectively dumping heat to the environment through the engine oil/air heat exchanger and the aircraft wing in a way which maximizes the fuel efficiency of the engine.
摘要翻译： 一种用于飞机旁通燃气轮机（涡轮风扇）发动机安装的程控热管理系统，其中发动机的燃料系统与发动机本身的油系统直接进行热交换关系，并且具有发动机驱动的发电机油系统， 通过相应的燃料/油热交换器，并且还与发动机机油/空气热交换器的发动机旁通空气装置的可变比例的选择性间接热交换关系。 燃料系统可在四种不同的燃料流动构型之间切换，以改变燃料系统和油系统之间的热量流动，其中两种燃料流动结构还涉及将燃料从发动机的燃料系统再循环到飞行器中的燃料箱 以使燃料系统与油箱的选择性热交换关系，从而使气流通过机翼。 通过选择适当的燃料流量结构并通过发动机油/空气热交换器和飞行器机翼选择性地将热量排放到环境中，以最大化燃料效率的方式来监测并保持在油和燃料系统中的温度并保持在预定限度内 发动机。
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公开(公告)号：US5152146A
公开(公告)日：1992-10-06
申请号：US829572
申请日：1992-02-03
申请人： Reginald J. Butler
发明人： Reginald J. Butler
CPC分类号： F02C7/14 , F02C7/232 , Y02T50/675
摘要： A fuel control valve arrangement is provided, which when connected to a number of fuel flow paths in the fuel system of a turbofan aeroengine, is capable of interconnecting them in several different fuel flow configurations as necessary to vary transport of heat around the fuel system. The valve arrangement has fuel ports as necessary to connect it to the fuel flow paths and transfer fuel between a diverter valve component and a fuel spill control valve component, each of which has independently translatable valve elements which are positionable to selectively prevent communication between the fuel ports. The spill control valve element is controllable to move progressively over a range of positions to throttle fuel flow to one of the ports and the connected fuel flow path which spills fuel back to a fuel supply tank.
摘要翻译： 提供了一种燃料控制阀装置，当与涡轮风扇发动机的燃料系统中的若干燃料流动路径连接时，能够根据需要将它们互连在几种不同的燃料流配置中，以改变燃料系统周围的热量传输。 阀装置具有必要的燃料端口以将其连接到燃料流动路径并且在分流阀部件和燃料溢出控制阀部件之间传输燃料，每个燃料端口具有可独立平移的阀元件，其可定位成选择性地防止燃料之间的连通 港口。 泄漏控制阀元件可控制地在一定范围的位置上逐渐移动，以节流燃料流向一个端口，以及连接的燃料流动路径，其将燃料喷射回燃料供应罐。
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公开(公告)号：US5241814A
公开(公告)日：1993-09-07
申请号：US863025
申请日：1992-04-03
申请人： Reginald J. Butler
发明人： Reginald J. Butler
CPC分类号： F02C7/14 , F02C7/232 , Y02T50/675
摘要： A program-controlled heat management system for an aircraft's bypass gas turbine (turbofan) engine installation, in which the engine's fuel system is put into direct heat exchange relationship with the engine's own oil system, and with an engine-driven electrical generator's oil system, by means of respective fuel/oil heat exchangers and also into selective indirect heat exchange relationship with a variable proportion of the engine's bypass air means of an engine oil/air heat exchanger. The fuel system is switchable between four different fuel flow configurations in order to vary the heat flows between the fuel system and the oil systems, two of the fuel flow configurations also involving recirculation of fuel from the engine's fuel system to a fuel tank in the aircraft wing in order to put the fuel system into selective heat exchange relationship with the tank and hence with the airstream passing over the wing. Temperatures in the oil and fuel systems are monitored and kept within predetermined limits by selecting the appropriate fuel flow configuration and selectively dumping heat to the environment through the engine oil/heat exchanger and the aircraft wing in a way which maximizes the fuel efficiency of the engine.
摘要翻译： 一种用于飞机旁通燃气轮机（涡轮风扇）发动机安装的程控热管理系统，其中发动机的燃料系统与发动机本身的油系统直接进行热交换关系，并且具有发动机驱动的发电机油系统， 通过相应的燃料/油热交换器，并且还与发动机机油/空气热交换器的发动机旁通空气装置的可变比例的选择性间接热交换关系。 燃料系统可在四种不同的燃料流动构型之间切换，以改变燃料系统和油系统之间的热量流动，其中两种燃料流动结构还涉及将燃料从发动机的燃料系统再循环到飞行器中的燃料箱 以使燃料系统与油箱的选择性热交换关系，从而使气流通过机翼。 通过选择适当的燃料流量结构并通过发动机油/热交换器和飞行器机翼选择性地将热量排放到环境中，以使发动机的燃料效率最大化的方式来监测和保持油和燃料系统中的温度并保持在预定限度内 。
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5.发明授权
公开(公告)号：US5121598A
公开(公告)日：1992-06-16
申请号：US503908
申请日：1990-04-04
申请人： Reginald J. Butler
发明人： Reginald J. Butler
CPC分类号： F02C7/14 , F02C7/232 , Y02T50/675
摘要： A program-controlled heat management system for an aircraft's bypass gas turbine (turbofan) engine installation, in which the engine's fuel system is put into direct heat exchange relationship with the engine's own oil system, and with an engine-driven electrical generators's oil system, by means of respective fuel/oil heat exchangers and also into selective indirect heat exchanger relationship with a variable proportion of the engine's bypass air means of an engine oil/air heat exchanger. The fuel system is switchable between four different fuel flow configurations in order to vary the heat flows between the fuel system and the oil systems, two of the fuel flow configurations also involving recirculation of fuel from the engine's fuel system to a fuel tank in the aircraft wing in order to put the fuel system into selective heat exchange relationship with the tank and hence with the airstream passing over the wing. Temperatures in the oil and fuel systems are monitored and kept within predetermined limits by selecting the appropriate fuel flow configuration and selectively dumping heat to the environment through the engine oil/air heat exchanger and the aircraft wing in a way which maximizes the fuel efficiency of the engine.
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