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11. 发明授权

US4120150A Compact fuel-to-air heat exchanger for jet engine application 失效
标题翻译：用于喷气发动机应用的紧凑型燃油对空气热交换器
公开(公告)号：US4120150A
公开(公告)日：1978-10-17
申请号：US797669
申请日：1977-05-17
申请人： Thomas G. Wakeman
发明人： Thomas G. Wakeman
IPC分类号： F02C7/18 , F02C7/224 , F02C7/22
CPC分类号： F02C7/185 , F02C7/224 , Y02T50/675
摘要： A structurally compact fuel-to-air heat exchanger, for a gas turbine engine, that permits a lower percentage of cooling air, than is presently needed in the art, to cool effectively the hot turbine, and its parts, of the engine. The heat exchanger includes: a plurality of flow tubes through which cool combustor fuel flows, with the flow tubes in a crossflow relationship with and to the hot flow of cooling air; an air manifolding and flow-directing system; and, a fuel manifolding and flow-directing system. The heat exchanger is uniquely disposed internal of the gas turbine engine, within the fire safe cavity, which is ventilated.
摘要翻译：用于燃气涡轮发动机的结构紧凑的燃料对空气热交换器允许比本领域目前需要的更低的冷却空气百分比来有效地冷却发动机的热涡轮机及其部件。热交换器包括：多个流管，冷却燃烧器燃料通过该流管，流管与冷却空气的热流交叉流动; 空气歧管和导流系统; 以及燃料歧管和导流系统。该热交换器独特地设置在燃气涡轮发动机的内部，在通风的消防安全空腔内。

12. 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。

13. 发明授权

US5165850A Compressor discharge flowpath 失效
标题翻译：压缩机排放流量
公开(公告)号：US5165850A
公开(公告)日：1992-11-24
申请号：US729956
申请日：1991-07-15
申请人： Brian J. Humke , Donald L. Bellia , Eric E. Baehre , Michael L. Barron , Thomas G. Wakeman
发明人： Brian J. Humke , Donald L. Bellia , Eric E. Baehre , Michael L. Barron , Thomas G. Wakeman
IPC分类号： F01D25/24 , F04D29/54 , F23R3/60
CPC分类号： F01D25/24 , F04D29/541 , F23R3/60
摘要： A compressor discharge flowpath for a gas turbine engine includes flowpath outer and inner walls joined to a plurality of circumferentially spaced flowpath dividers extending therebetween. An inner support extends from the inner wall and is joined to a turbine nozzle, and an outer support extends from the outer wall and is joined to an engine casing. The outer support preferably includes a plurality of circumferentially spaced beams being sized and configured for carrying both axial force and torque transmitted therethrough from the turbine nozzle to the casing while allowing the beams to bend radially for accommodating differential thermal movement between the casing and the outer wall.

14. 发明授权

US4796423A Sheet metal panel 失效
标题翻译：钣金面板
公开(公告)号：US4796423A
公开(公告)日：1989-01-10
申请号：US4827
申请日：1987-01-12
申请人： Louis Lievestro , James S. Kelm , Arthur L. Ludwig , Harvey M. Maclin , Thomas G. Wakeman
发明人： Louis Lievestro , James S. Kelm , Arthur L. Ludwig , Harvey M. Maclin , Thomas G. Wakeman
IPC分类号： F01D9/04 , F02G1/00 , F02G3/00
CPC分类号： F01D9/04 , Y10T403/4327 , Y10T403/7016
摘要： A sheet metal panel comprising a bent region is disclosed. The region defines a first arc of intersection with a first plane and a second arc of intersection with a second plane. The second arc has a radius of less than twice the thickness of the panel.
摘要翻译：公开了一种包括弯曲区域的金属板。该区域定义与第一平面和第二平面相交的第一弧线的第一交叉圆弧。第二弧的半径小于面板厚度的两倍。

15. 发明授权

US5601402A Turbo machine shroud-to-rotor blade dynamic clearance control 失效
标题翻译：涡轮机护罩对转子叶片的动态间隙控制
公开(公告)号：US5601402A
公开(公告)日：1997-02-11
申请号：US874201
申请日：1986-06-06
申请人： Thomas G. Wakeman , Robert J. Corsmeier
发明人： Thomas G. Wakeman , Robert J. Corsmeier
IPC分类号： F01D11/22 , F01D11/08
CPC分类号： F01D11/22
摘要： A clearance control arrangement for the rotor blade-to-stator shroud clearance in an aircraft engine or other turbo machine. The disclosed arrangements use large area piston-like structures located circumferential to the turbo machine and capable of operation from pressures developed within the machine. One disclosed arrangement incorporates static adjustment capability that can be disposed to provide symmetrical or asymmetrical clearances. The disclosed clearance control can be used as a fast-acting supplement or in lieu of other clearance control arrangements and is arranged to be actuated upon sensing the onset of rotor-to-stator collision pinch point conditions in the turbo machine.
摘要翻译：一种用于飞行器发动机或其他涡轮机中的转子叶片到定子护罩间隙的间隙控制装置。所公开的布置使用位于涡轮机周向的大面积活塞式结构，并能够从机器内产生的压力进行操作。一个公开的布置包括静态调整能力，其可被设置成提供对称或不对称的间隙。公开的间隙控制可以用作快速补充或代替其它间隙控制装置，并且被布置成在感测涡轮机中转子到定子碰撞夹点状态的开始时被致动。

16. 发明授权

US5154372A Torque multiplier for aircraft propeller 失效
标题翻译：飞机螺旋桨扭矩乘数
公开(公告)号：US5154372A
公开(公告)日：1992-10-13
申请号：US556676
申请日：1990-07-23
申请人： Peter Hora , David E. Bulman , Thomas C. Hermans , Thomas G. Wakeman , Walter D. Howard
发明人： Peter Hora , David E. Bulman , Thomas C. Hermans , Thomas G. Wakeman , Walter D. Howard
IPC分类号： F01D1/24
CPC分类号： F01D1/24 , B64C11/306 , B64C11/32 , B64D2027/005 , F05D2200/13 , Y02T50/66 , Y02T50/671
摘要： The invention concerns aircraft propellers of the variable pitch type. Each propeller blade is carried by a trunnion which is rotatably mounted to a common ring. Each trunnion contains a reduction gear set which is driven by a radial shaft. The reduction gear sets multiply the torque applied by the shafts, thus allowing shafts of reduced diameter to be used. The reduced diameter is important when the shafts must pass through a turbine flowpath, and thus be concealed within turbine blades. The reduced diameter shafts can be easily concealed within turbine blades without redesigning and compromising blade aerodynamics.
摘要翻译：本发明涉及可变螺距类型的飞机螺旋桨。每个螺旋桨叶片由可旋转地安装到公共环的耳轴承载。每个耳轴都包含由径向轴驱动的减速齿轮组。减速装置乘以由轴施加的扭矩，从而允许使用减小直径的轴。当轴必须通过涡轮流动路径并因此被隐藏在涡轮机叶片内时，减小的直径是重要的。减小直径的轴可以容易地隐藏在涡轮叶片内，而不会重新设计并损害叶片空气动力学。

17. 发明授权

US5050803A Actuation system for positioning a vectoring exhaust nozzle 失效
标题翻译：定位导向排气喷嘴的驱动系统
公开(公告)号：US5050803A
公开(公告)日：1991-09-24
申请号：US420413
申请日：1989-10-12
申请人： Thomas G. Wakeman , Thomas S. Clayton , Conrad D. Wagenknecht
发明人： Thomas G. Wakeman , Thomas S. Clayton , Conrad D. Wagenknecht
IPC分类号： F02K1/12 , F02K1/00 , F02K1/62
CPC分类号： F02K1/62 , F02K1/006 , F05D2260/15 , Y02T50/671
摘要： A simplified actuation system for positioning the divergent flaps of a vectorable two-dimensional exhaust nozzle is disclosed. The system includes lever arms having cam surfaces pivotably attached to diverent flap crank shafts. An actuator is pinned to the nozzle sidewall and operably connected to a slider bar which has two cam followers at either end which are fixed with respect to each other and enage the cam surfaces of the lever arms. The slider bar is slideably engaged to the nozzle sidewall so as to permit radial movement with respect to the nozzle centerline. As the convergent flaps are moved the lever arms are translated axially and the cam followers in cooperation with the cam surfaces on the lever arms schedule the relative angle between the divergent flaps and thereby the exit area of the nozzle. Vectoring is provided operating the actuators which translate the cam followers in the radial direction, up or down, thereby rotating the divergent flaps so that they are pitched up or down in unison.
摘要翻译：公开了一种用于定位可引导的二维排气喷嘴的发散板的简化的致动系统。该系统包括杠杆臂，其具有可枢转地附接到潜水式翼片曲轴的凸轮表面。致动器被固定到喷嘴侧壁并且可操作地连接到滑块，该滑杆具有两端的两个凸轮从动件，该两个凸轮从动件相对于彼此固定并且使杠杆臂的凸轮表面成为可能。滑块可滑动地接合到喷嘴侧壁，以便允许相对于喷嘴中心线的径向移动。当收敛的翼片移动时，杆臂被轴向平移，并且凸轮从动件与杆臂上的凸轮表面协调调节发散翼片之间的相对角度，从而调节喷嘴的出口面积。提供矢量操作，使致动器沿径向向上或向下平移凸轮从动件，从而使发散片旋转使得它们一致地向上或向下倾斜。

18. 发明授权

US5039278A Power turbine ventilation system 失效
标题翻译：动力涡轮通风系统
公开(公告)号：US5039278A
公开(公告)日：1991-08-13
申请号：US336374
申请日：1989-04-11
申请人： Thomas G. Wakeman , Richard W. Brown
发明人： Thomas G. Wakeman , Richard W. Brown
IPC分类号： F02C7/18 , F01D7/00 , F02C3/067 , F04D29/32 , F04D29/58
CPC分类号： F04D29/323 , F01D7/00 , F04D29/584 , F05D2260/74 , F05D2260/76
摘要： Air control mechanism within a power turbine section of a gas turbine engine. The power turbine section includes a rotor and at least one variable pitch propulsor blade. The propulsor blade is coupled to and extends radially outwardly of the rotor. A first annular fairing is rotatable with the propulsor blade and interposed between the propulsor blade and the rotor. A second fairing is located longitudinally adjacent to the first fairing. The first fairing and the second fairing are differentially rotatable. The air control mechanism includes a platform fixedly coupled to a radially inner end of the propulsor blade. The platform is generally positioned in a first opening and a first fairing. The platform and the first fairing define an outer space. In a first position corresponding with a first propulsor blade pitch, the platform is substantially conformal with the first fairing. In a second position corresponding with the second propulsor blade pitch, an edge portion of the platform is displaced radially outwardly from the first fairing. When the blades are in the second position and rotating about the engine axis, the displacement of the edge portion with respect to the first fairing allows air to flow from the outer space to the annular cavity.
摘要翻译：燃气涡轮发动机的动力涡轮机部分内的空气控制机构。动力涡轮机部分包括转子和至少一个可变螺距推进式叶片。推进器叶片联接到转子的径向外侧并且向其延伸。第一环形整流罩可以与推进器叶片一起旋转并插入推进器叶片和转子之间。第二个整流罩位于第一个整流罩的纵向相邻处。第一个整流罩和第二个整流罩是有差异的。空气控制机构包括固定地联接到推进式叶片的径向内端的平台。平台通常位于第一开口和第一整流罩中。平台和第一个整流罩定义了一个外部空间。在与第一推进器叶片间距对应的第一位置中，平台基本上与第一整流罩共形。在与第二推进器叶片间距对应的第二位置，平台的边缘部分从第一整流罩径向向外位移。当叶片处于第二位置并围绕发动机轴线旋转时，边缘部分相对于第一整流罩的位移允许空气从外部空间流动到环形空腔。

19. 发明授权

US4679400A Variable turbine vane support 失效
标题翻译：可变涡轮叶片支架
公开(公告)号：US4679400A
公开(公告)日：1987-07-14
申请号：US754678
申请日：1985-07-12
申请人： James S. Kelm , Harvey M. Maclin , Edward C. Vickers , Thomas G. Wakeman
发明人： James S. Kelm , Harvey M. Maclin , Edward C. Vickers , Thomas G. Wakeman
IPC分类号： F01D17/16 , F23R3/60 , F02C1/00
CPC分类号： F01D17/162 , F23R3/60
摘要： Means for axially attaching a variable turbine vane array to a combustor in a gas turbine engine is disclosed. The attachment means are configured so that substantially all of the axial load on the array is transmitted through the walls of the combustor.
摘要翻译：公开了用于将可变涡轮叶片阵列轴向附接到燃气涡轮发动机中的燃烧器的装置。附接装置被构造成使得阵列上的基本上所有的轴向负载都通过燃烧器的壁传递。

20. 发明授权

US4628694A Fabricated liner article and method 失效
公开(公告)号：US4628694A
公开(公告)日：1986-12-16
申请号：US562959
申请日：1983-12-19
申请人： James S. Kelm , Arthur L. Ludwig , Harvey M. Maclin , Steven K. Roggenkamp , Thomas G. Wakeman
发明人： James S. Kelm , Arthur L. Ludwig , Harvey M. Maclin , Steven K. Roggenkamp , Thomas G. Wakeman
IPC分类号： B21D35/00 , F23R3/00 , F02C7/00
CPC分类号： F23R3/002 , B21D35/00 , F05B2260/201 , F23R2900/00018
摘要： A method of fabricating sheet metal panels and the article produced thereby. According to one form, the method of fabrication includes the steps of providing a panel of sheet metal, perforating the panel to provide a plurality of holes, forming the panel into a preselected curve about a longitudinal centerline, forming the leading edge portion of the panel into a front flange, forming a shoulder in the panel centered on the holes and extending perpendicularly from a surface thereof, bending an outer portion of the shoulder into a lip, and bonding the portions of the panel comprising the shoulder and lip.

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