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1. 发明授权

US5320307A Aircraft engine thrust mount 失效
标题翻译：飞机发动机推力安装
公开(公告)号：US5320307A
公开(公告)日：1994-06-14
申请号：US857136
申请日：1992-03-25
申请人： Hahn M. Spofford , Thomas G. Wakeman , Donald L. Bellia , Thomas P. Joseph , Gregg H. Wilson , James E. Cencula , Frederick W. Tegarden , Michael H. Schneider
发明人： Hahn M. Spofford , Thomas G. Wakeman , Donald L. Bellia , Thomas P. Joseph , Gregg H. Wilson , James E. Cencula , Frederick W. Tegarden , Michael H. Schneider
IPC分类号： B64D27/10 , B64D27/18 , B64D27/26 , F02C7/20
CPC分类号： B64D27/18 , B64D27/26 , B64D2027/266 , B64D2027/268 , Y02T50/44
摘要： An aircraft engine thrust mount includes a pair of spaced apart thrust links pivotally joined at one end to an engine first frame and at opposite ends to a lever. A platform is fixedly joined to an aircraft pylon and includes first and second spaced apart clevises and a center clevis therebetween. The center clevis is pivotally joined to a center of the lever for carrying thrust force from the first frame through both thrust links and to the platform and pylon during normal operation. A pair of pins pivotally join the thrust links to the lever and extend through apertures in the platform first and second clevises to define predetermined gaps therebetween for allowing the lever to rotate relative to the platform center clevis up to a predetermined angular rotation. In a failure mode of operation the pins contact the platform first and second clevises for transmitting thereto either tension or compression thrust loads for providing an alternate failsafe loadpath. In a preferred embodiment, the platform further includes an aft mount joined to an engine second frame spaced aft of the engine first frame.
摘要翻译：飞机发动机推力支架包括一对间隔开的推力连杆，其一端枢转地连接到发动机第一框架，并且在相对的端部处连接到杠杆。平台固定地连接到飞机托架，并且包括第一和第二间隔开的U形夹和在它们之间的中心U形夹。中心U形夹被枢转地连接到杠杆的中心，用于在正常操作期间通过两个推力连杆承载来自第一框架的推力以及平台和塔架。一对销枢转地将推力连接件连接到杠杆并延伸穿过平台中的孔，并且第二和第二夹具在其间限定预定的间隙，以允许杆相对于平台中心U形夹旋转到预定的角度旋转。在故障操作模式中，销与第一和第二托架接触，用于向其传递用于提供备用故障安全加载路径的张力或压缩推力载荷。在优选实施例中，平台还包括接合到发动机第一框架后方间隔开的发动机第二框架的后部安装座。

2. 发明授权

US5275357A Aircraft engine mount 失效
标题翻译：飞机发动机支架
公开(公告)号：US5275357A
公开(公告)日：1994-01-04
申请号：US821376
申请日：1992-01-16
申请人： Laurence Seelen , Thomas P. Joseph , James E. Cencula , Donald L. Bellia , Hahn M. Spofford
发明人： Laurence Seelen , Thomas P. Joseph , James E. Cencula , Donald L. Bellia , Hahn M. Spofford
IPC分类号： B64D27/26 , B64D27/00 , F02C7/20
CPC分类号： B64D27/26 , B64D2027/266
摘要： An aircraft engine mount includes a frame fixedly joined in a gas turbine engine and a platform fixedly joined to an aircraft wing or tail pylon. A first beam is pivotally joined to the frame and the platform at first and second joints, respectively. The first beam is additionally joined to the platform at a third joint which allows longitudinal movement between the first beam and the platform at the third joint while preventing rotation of the first beam. A second beam is spaced from the first beam and is pivotally joined to the frame and platform at fourth and fifth joints, respectively, and is additionally joined to the platform at a sixth joint for allowing limited rotation of the second beam during normal operation while preventing rotation of the second beam upon a failure of the first beam to carry load.
摘要翻译：飞机发动机支架包括固定连接在燃气涡轮发动机中的框架和固定地连接到飞机机翼或尾塔的平台。第一梁分别在第一和第二关节处枢转地连接到框架和平台。第一梁在第三关节处另外连接到平台，其允许在第三关节处的第一梁和平台之间的纵向运动，同时防止第一梁的旋转。第二梁与第一梁隔开并且分别在第四和第五关节处枢转地连接到框架和平台，并且在第六关节处另外连接到平台，用于允许在正常操作期间第二梁的有限旋转，同时防止第一光束在第一光束发生故障时携带负载时的第二光束的旋转。

3. 发明授权

US5303880A Aircraft engine pin mount 失效
标题翻译：飞机发动机引脚安装
公开(公告)号：US5303880A
公开(公告)日：1994-04-19
申请号：US967355
申请日：1992-10-28
申请人： James E. Cencula , Donald L. Bellia , Hahn M. Spofford
发明人： James E. Cencula , Donald L. Bellia , Hahn M. Spofford
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/266
摘要： An aircraft engine mounting assembly using a clevis type joint to connect a link is provided with a mounting pin assembly disposed in an aperture of the link having inexpensive and easily replaceable concentric inner and outer non-rotational bushings surrounding a conventional pin and corresponding oppositely disposed sets of inner flat contact surfaces on the outer surface of inner bushing and outer flat contact surfaces on the inner surface of the outer bushing which provide reduced contact stresses between the pin and the aperture as compared to conventional assemblies. The contact surfaces are in general sliding engagement in the longitudinal direction and are provided with clearances between the inner and outer bushings in the longitudinal and transverse directions to allow for thermal growth of the engine.
摘要翻译：具有使用U形夹型接头连接连杆的飞行器发动机安装组件设置有安装销组件，该安装销组件设置在链节的孔中，该安装销组件具有便宜且易于更换的同心的内外非旋转衬套，其围绕常规销和对应的相对设置的组在内衬套的外表面上的内平面接触表面和外套筒内表面上的外平面接触表面，与常规组件相比，提供销和孔之间的接触应力减小。接触表面在纵向方向上通常滑动接合，并且在纵向和横向方向上在内衬套和外衬套之间设置有间隙，以允许发动机的热增长。

4. 发明授权

US5277382A Aircraft engine forward mount 失效
标题翻译：飞机发动机前进
公开(公告)号：US5277382A
公开(公告)日：1994-01-11
申请号：US959885
申请日：1992-10-13
申请人： Laurence Seelen , Thomas P. Joseph , Hahn M. Spofford , Charles S. Orkiszewski
发明人： Laurence Seelen , Thomas P. Joseph , Hahn M. Spofford , Charles S. Orkiszewski
IPC分类号： B64D27/26 , B64D27/00
CPC分类号： B64D27/26 , B64D2027/266
摘要： An aircraft engine mount includes an annular casing fixedly disposed in the engine, a mounting platform spaced radially outwardly from the casing and fixedly joinable to an aircraft pylon, and a pair of circumferentially spaced apart links pivotally joined to the platform and the casing at respective radially outer and inner joints. The inner joints are circumferentially spaced closer together than the outer joints so that the intersection point of the longitudinal axes of the two links is disposed radially below the two links themselves for reducing lateral deflection of the casing relative to the engine mount.
摘要翻译：飞机发动机支架包括固定地设置在发动机中的环形壳体，与壳体径向向外间隔开并且可固定地连接到飞机吊架的安装平台，以及一对周向间隔开的连接件，其在径向上以相应的方式枢转地连接到平台和壳体外关节。内部接头与外部接头周向间隔开更靠近在一起，使得两个连杆的纵向轴线的交点位于两个连杆本身的径向下方，以减小壳体相对于发动机支架的横向偏转。

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