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1. 发明授权

US4437627A Integrated power plant installation system 失效
标题翻译：综合电站安装系统
公开(公告)号：US4437627A
公开(公告)日：1984-03-20
申请号：US357746
申请日：1982-03-12
申请人： James R. Moorehead
发明人： James R. Moorehead
IPC分类号： B64D27/18 , B64D33/00
CPC分类号： B64D27/18 , B64D33/00 , B64D2027/264
摘要： An integrated power plant installation system for underwing high-bypass mid-length fan air duct core-mounted engines readily permits disconnection of the entire powerplant at the wing thereby virtually eliminating the necessity of disconnecting the engine and complex systems per se from the support strut when engine replacement or removal proves necessary. Excessive congestion within the vicinity of the strut box structure is eliminated by disposing the engine accessories, and auxiliary equipment and system lines, within the lower quadrant of the powerplant assembly in both a laterally and longitudinally distributed array. Potential catastrophic fire hazards within the nacelle are substantially eliminated by routing the fluid lines and electrical conduits axially aft and upwardly around the circumference of the engine within the nozzle section of the powerplant aft of all rotating discs. These latter features permit the utilization of a simplified strut box structure in that the same need not be provided with equipment clearance structure, conduit throughbores, and complex fire seals and drains. The strut structure is easily tunable with simple plate structure for flutter stiffness control, involving strut and wing bending in gusts. The wing attach/detach engine mounting system, particularly for a core-mounted engine by means of the simplified strut box structure, also facilitates the elimination of the conventional fan D, or split, duct system and enables the employment of a continuous hoop structure thrust reverser system.
摘要翻译：用于底部高旁路中长风扇风道核心安装发动机的集成发电厂安装系统易于允许机翼上的整个动力装置断开，从而实际上消除了将发动机和复杂系统本身与支撑支柱断开的必要性，发动机更换或拆卸证明是必要的。通过将发动机附件和辅助设备和系统线路布置在动力装置组件的下部象限的横向和纵向分布的阵列中，可以消除支柱结构附近的过度拥塞。通过在所有旋转盘的动力装置后部的喷嘴部分内沿着发动机的圆周方向将流体管线和电气导管轴向向后轴向布置，从而基本上消除了机舱内潜在的灾难性火灾危险。这些后面的特征允许利用简化的支柱结构，因为不需要设备间隙结构，导管通孔和复杂的防火密封和排水沟。支柱结构易于调整，具有简单的板结构，用于颤振刚度控制，涉及阵风和翼阵弯曲。机翼安装/拆卸发动机安装系统，特别是通过简化支柱结构的内置发动机，也有助于消除传统的风扇D或分流管道系统，并且能够使用连续的环形结构推力反向系统。

2. 发明授权

US4252286A Simplified core flow thrust control device 失效
标题翻译：简化核心流量推力控制装置
公开(公告)号：US4252286A
公开(公告)日：1981-02-24
申请号：US030266
申请日：1979-04-16
申请人： James R. Moorehead
发明人： James R. Moorehead
IPC分类号： B64D33/04 , F02K1/58 , B64C15/00 , F02K1/54
CPC分类号： B64D33/04 , F02K1/58 , Y02T50/671
摘要： There is disclosed a simplified, lightweight, easily stowed thrust control device for the hot core exhaust flow of a jet engine. The device is mounted in the engine strut fairing, downstream of the nozzle exit plane to reduce exposure to the high exhaust temperatures. In a blocking position, the mounting hardware, actuator and actuator linkage is located so as to be cooled by both free stream and fan air, providing a longer operating life, less maintenance and more reliable operation. Simplified construction and mounting arrangement permit the device to be readily retrofitted on existing installations.
摘要翻译：公开了一种用于喷气发动机的热芯排气流的简化的，轻便的，容易收起的推力控制装置。该装置安装在发动机支柱整流罩中，在喷嘴出口平面的下游，以减少暴露于高排气温度。在阻塞位置，安装硬件，执行器和执行器联动装置被定位以便通过自由流和风扇空气来冷却，提供更长的使用寿命，更少的维护和更可靠的操作。简化的结构和安装布置使得设备可以在现有的设备上进行改装。

3. 发明授权

US4044973A Nacelle assembly and mounting structures for a turbofan jet propulsion engine 失效
标题翻译：涡轮风扇喷气推进发动机的机舱组件和安装结构
公开(公告)号：US4044973A
公开(公告)日：1977-08-30
申请号：US644915
申请日：1975-12-29
申请人： James R. Moorehead
发明人： James R. Moorehead
IPC分类号： B64D27/20 , B64D27/26 , B64D29/06
CPC分类号： B64D27/26 , B64D27/20
摘要： A nacelle assembly including an inlet channel, an exterior cowl, a fan channel, and a turbine exhaust nozzle is directly mounted on a turbofan jet propulsion engine. The engine in turn is shock mounted directly on a strut, in turn affixed to an aircraft. A central portion of the outer cowl is hinged to open in a clam shell manner about hinges positioned adjacent the strut location to expose the fan casing and engine accessories for maintenance and removal. A rearward portion of the nacelle assembly is formed in two D-duct structures that are also hinged to open in a clam shell manner about hinges positioned adjacent the strut location. The D-duct structures include portions of the outer cowl and of the fan duct walls. When the D-duct structures are open, the turbine casing of the turbofan engine is exposed for maintenance, repair and removal. A pair of beams, affixed at one end to the aircraft fuselage, and enclosed by an aerodynamic fairing, constitute the mounting strut. The beams extend beyond the fairing into the nacelle and through a fan duct bifurcating structure. The forward of the two beams forks into a yoke-like structure that surrounds a portion of and is affixed by shock mounts to the exterior of the fan casing. The rear beam is also affixed to the turbine casing by a shock mount.
摘要翻译：包括入口通道，外部整流罩，风扇通道和涡轮机排气喷嘴的机舱组件直接安装在涡轮风扇喷气推进发动机上。发动机又是直接冲击支撑在支柱上，反过来又固定在一架飞机上。外罩的中心部分铰接成以蛤壳方式围绕位于支柱位置附近的铰链打开，以暴露风扇壳体和发动机附件以进行维护和拆卸。机舱组件的后部形成在两个D形管道结构中，其还铰接成以蛤壳方式围绕位于支柱位置附近的铰链打开。 D管结构包括外罩和风扇管壁的部分。当D-管道结构打开时，涡轮风扇发动机的涡轮机壳体被暴露以进行维护，修理和拆卸。一对梁，一端固定在飞机机身上，并被气动整流罩包围，构成安装支柱。梁延伸超过整流罩进入机舱，并通过风扇管道分叉结构。两个梁的前部叉入围绕一部分的轭状结构，并通过减震器固定到风扇壳体的外部。后梁还通过防震架固定到涡轮机壳体。

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