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公开(公告)号：US4132069A
公开(公告)日：1979-01-02
申请号：US753452
申请日：1976-12-22
IPC分类号： F02C7/04 , B64D27/18 , B64D29/00 , F02C7/20 , F02K3/00 , F02K3/04 , F02K3/06 , F02C3/06 , F02K1/20
CPC分类号： F02C7/20 , B64D27/18 , B64D29/00 , F04D29/526 , F04D29/685 , Y02T50/44 , Y02T50/672 , Y10T137/0536
摘要： A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus while the outer surface of the nacelle defines a streamlined envelope for the engine.
摘要翻译： 与燃气涡轮发动机一起使用的机舱设置有类似于轮辐的整体网状结构，用于刚性地连接机舱和发动机。 机舱通过蹼状结构与发动机的空间关系完全支撑。 机舱的内表面限定了发动机运动流体流动环的外部限制，而机舱的外表面限定了发动机的流线型封套。
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公开(公告)号：US4055041A
公开(公告)日：1977-10-25
申请号：US628221
申请日：1975-11-03
摘要： A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus while the outer surface of the nacelle defines a steamlined envelope for the engine.
摘要翻译： 与燃气涡轮发动机一起使用的机舱设置有类似于轮辐的整体网状结构，用于刚性地连接机舱和发动机。 机舱通过蹼状结构与发动机的空间关系完全支撑。 机舱的内表面限定了发动机运动流体流动环的外部限制，而机舱的外表面限定了发动机的蒸汽封套。
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公开(公告)号：US4068470A
公开(公告)日：1978-01-17
申请号：US522109
申请日：1974-11-08
CPC分类号： F02C7/32 , Y02T50/672 , Y10T74/19521 , Y10T74/19665
摘要： Drive means for connecting a gas turbine engine to its accessories are so constructed as to allow the accessories to be selectively positioned to any one of several predetermined circumferential positions about the perimeter of the engine. This feature permits convenient mounting of the same engine upon vehicles demanding radically different engine mounting arrangements.
摘要翻译： 用于将燃气涡轮发动机连接到其附件的驱动装置被构造成允许附件被选择性地定位到围绕发动机的周边的几个预定圆周位置中的任何一个。 该特征允许将相同的发动机方便地安装在要求完全不同的发动机安装布置的车辆上。
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公开(公告)号：US4446696A
公开(公告)日：1984-05-08
申请号：US278924
申请日：1981-06-29
CPC分类号： F02C6/206 , F02C7/36 , F02K3/077 , F05D2220/324 , F05D2220/327 , Y02T50/671
摘要： A compound propulsor for powering a vehicle, such as an aircraft. A compound propulsor includes a core gas turbine engine, a fan encased within a cowl, at least one propeller, and drive means for distributing a portion of the power produced by the core engine to the fan and another portion to the propeller. Preferably, the compound propulsor also includes variable geometry inlet guide vanes for varying the portions of power distributed to the fan and propeller.
摘要翻译： 用于为诸如飞机的车辆供电的复合推进器。 复合推进器包括核心燃气涡轮发动机，封装在整流罩内的风扇，至少一个螺旋桨，以及驱动装置，用于将由核心发动机产生的功率的一部分分配到风扇，另一部分分配到螺旋桨。 优选地，复合推进器还包括可变几何形状的入口引导叶片，用于改变分配到风扇和螺旋桨的功率的部分。
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公开(公告)号：US4038817A
公开(公告)日：1977-08-02
申请号：US582606
申请日：1975-06-02
CPC分类号： B64D37/26 , Y02T50/44 , Y10T137/87772
摘要： Fuel is selectively jettisoned through the engine of an aircraft by way of a normally closed, solenoid-operated jettison valve which is fed from the boost pump in the engine fuel system. The jettison valve is servo activated by the main fuel flow so that the engine must be running for the opening of the solenoid valve to occur. For an engine having an augmenter, other interlocks are provided to prevent the jettison of fuel when the augmenter is in use and to preclude the ignition function to the augmenter while fuel is being jettisoned.
摘要翻译： 通过在发动机燃料系统中从增压泵供给的常闭电磁操作的喷射阀，将燃料选择性地排出飞机的发动机。 喷射阀由主燃料流动被伺服启动，使得发动机必须运行才能使电磁阀的打开发生。 对于具有增压器的发动机，提供其他联锁装置以防止当增压器在使用时喷射燃料，并且在燃料被排出时排除对增压器的点火功能。
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公开(公告)号：US4147029A
公开(公告)日：1979-04-03
申请号：US731664
申请日：1976-10-13
申请人： Donald F. Sargisson
发明人： Donald F. Sargisson
CPC分类号： F02C7/042 , F02C7/20 , F02K1/386 , F02K1/70 , Y10T137/0536
摘要： A gas turbine engine is provided with a long nacelle which forms both the inlet and exhaust of the engine. The nacelle is spaced apart from a core engine to define an annular bypass duct therebetween. The incoming air stream is pressurized by a front fan disposed in the inlet and then divided between the core engine and bypass duct. A lobed mixer device is provided downstream of the core engine to intermix the core engine and bypass duct exhaust streams. The mixed streams are discharged from a common nozzle formed at the downstream end of the nacelle. A non-redundant system of mounts are provided to secure the engine to the pylon of an aircraft in such a manner as to reduce engine thrust induced bending loads and insure symmetry of these thrust loads. The total reaction of the thrust loads at the mounting points is reduced by a unique interlocking system by which all of the major engine assemblies are joined. The engine is configured such that it may be easily removed from an aircraft and replaced with a spare engine in minimum time. This quick change capability is achieved by mounting the engine such that it may be removed from the aircraft by disconnecting the forward and rear mounts and an engine bleed duct. The mid portion of the engine nacelle and all accessories mounted thereon remain with the aircraft.
摘要翻译： 燃气涡轮发动机设置有形成发动机的入口和排气两者的长机舱。 机舱与核心发动机间隔开，以在它们之间限定环形旁路管道。 进入的空气流由设置在入口中的前风扇加压，然后在核心发动机和旁路管道之间分配。 在核心发动机的下游设置有一个叶片混合装置，以使核心发动机和旁路管道废气流混合。 混合流从形成在机舱下游端的公共喷嘴排出。 提供非冗余的安装系统以将发动机固定在飞机的塔架上，以减少发动机推力引起的弯曲载荷并确保这些推力载荷的对称性。 通过独特的联锁系统减少安装点处的推力负载的总反应，所有的主要发动机组件都通过该互锁系统连接。 发动机被配置为使得其可以容易地从飞行器移除并且在最短时间内用备用发动机替换。 这种快速更换能力是通过安装发动机来实现的，使得可以通过断开前部和后部支架以及发动机排放管道从飞机上移除。 发动机舱的中部和安装在其上的所有附件都保留在飞机上。
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公开(公告)号：US4142365A
公开(公告)日：1979-03-06
申请号：US737786
申请日：1976-11-01
CPC分类号： F02K3/077 , F02K1/386 , F02K3/04 , Y02T50/671
摘要： A high bypass ratio gas turbofan engine provided with a hybrid mixer for mixing that portion of the bypass stream equivalent to a bypass ratio of substantially two with the core engine hot gas stream. The mixture is passed through a common exhaust nozzle.
摘要翻译： 具有混合混合器的高旁路比气体涡轮风扇发动机，用于将相当于二级旁路比的旁路流的那部分与核心发动机热气流混合。 混合物通过一个普通的排气喷嘴。
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公开(公告)号：US4556366A
公开(公告)日：1985-12-03
申请号：US542868
申请日：1983-10-17
CPC分类号： H02K7/1823 , B64C11/44 , Y10S416/04
摘要： A propeller engine system with means for generating electric power within a rotatable hub is disclosed. The means include a shaft extending into the hub so that the hub and shaft are differentially rotatable. Magnetic means are fixed to the shaft and winding means are fixed to the hub so that either rotation of the rotor shaft or hub induces an electric current in the winding means.
摘要翻译： 公开了一种具有用于在可旋转轮毂内产生电力的装置的螺旋桨发动机系统。 该装置包括延伸到毂中的轴，使得轮毂和轴能够差异地旋转。 磁性装置固定在轴上，并且绕组装置固定到轮毂上，使得转子轴或轮毂的旋转在绕组装置中产生电流。
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公开(公告)号：US4240252A
公开(公告)日：1980-12-23
申请号：US870709
申请日：1978-01-19
CPC分类号： F02K1/386
摘要： In a mixed flow gas turbine engine of the type which includes an outer nacelle spaced apart from a core engine to define an annular bypass duct therebetween, there is provided a convoluted lobed mixer having a plurality of cold chutes in flow communication with the bypass duct and hot chutes in flow communication with the core engine. In order to suppress engine turbomachinery and exhaust noise, the mixer is alternatively provided with various combinations of acoustically treated lobes, spool pieces, radial splitters, and/or circumferential splitters. These acoustic treatments act in conjunction with an acoustically treated nozzle assembly and an acoustically treated plug assembly to provide an effective low aerodynamic pressure loss noise suppression system.
摘要翻译： 在这种类型的混合气体燃气涡轮发动机中，其包括与核心发动机间隔开的外部机舱，以在它们之间限定环形旁路管道，其中提供了一个回旋叶片混合器，其具有与旁通管道流动连通的多个冷滑槽， 与核心发动机流通的热槽。 为了抑制发动机涡轮机械和排气噪声，混合器可替换地提供有声处理的叶片，卷轴件，径向分离器和/或周向分离器的各种组合。 这些声学处理与声学处理的喷嘴组件和声处理的塞子组件一起作用，以提供有效的低空气动力学压力损失噪声抑制系统。
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