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1. 发明授权

US4000612A Cooling system for a thrust vectoring gas turbine engine exhaust system 失效
标题翻译：推力矢量化燃气轮机发动机排气系统的冷却系统
公开(公告)号：US4000612A
公开(公告)日：1977-01-04
申请号：US599644
申请日：1975-07-28
申请人： Thomas G. Wakeman , Dudley O. Nash
发明人： Thomas G. Wakeman , Dudley O. Nash
IPC分类号： F02K1/12 , B64D33/08 , F02K1/00 , F02K1/60 , F02K1/78 , F02K1/20 , F02K11/04
CPC分类号： F02K1/006 , Y02T50/671
摘要： A thrust vectoring gas turbine engine exhaust nozzle is provided with a variable area flow path wherein cooling of the stationary flow path side walls is partially obtained by the film cooling technique. Regulating means, such as a valve, is provided to control the pressure drop of the cooling fluid across the walls as a function of nozzle flow path area, thus optimizing the coolant flow rate as a function of flow path area. Where a rotating bonnet-type deflector is employed to divert the exhaust stream downward to obtain a vertical take-off and landing capability, a system is provided to cool the deflector walls by both the impingement and convection cooling techniques. A favorable pressure gradient for the cooling fluid is obtained by exhausting the cooling fluid to ambient pressure whenever the deflector is deployed. Another valve is provided to regulate the flow of coolant to an expansion flap when the deflector is in its stowed position external to the flow path.
摘要翻译：推力矢量化燃气轮机发动机排气喷嘴设置有可变区域流动路径，其中通过膜冷却技术部分地获得固定流路侧壁的冷却。提供诸如阀门的调节装置，以便根据喷嘴流动路径面积来控制冷却流体穿过壁的压降，从而优化作为流路面积的函数的冷却剂流量。在使用旋转阀盖型偏转器将排气流向下转移以获得垂直起飞和着陆能力的情况下，提供系统以通过冲击和对流冷却技术来冷却偏转器壁。每当偏转器被展开时，通过将冷却流体排放到环境压力来获得冷却流体的有利的压力梯度。另一个阀被设置成当偏转器处于其位于流动路径外部的收起位置时调节冷却剂到膨胀瓣的流动。

2. 发明授权

US5370427A Expansion joint for fluid piping with rotation prevention member 失效
标题翻译：带旋转防止件的流体管道膨胀节
公开(公告)号：US5370427A
公开(公告)日：1994-12-06
申请号：US179286
申请日：1994-01-10
申请人： James S. Hoelle , Ivan H. Peterson , Thomas G. Wakeman , Michael R. Storage , Michael A. Umney , Mark K. Meyer
发明人： James S. Hoelle , Ivan H. Peterson , Thomas G. Wakeman , Michael R. Storage , Michael A. Umney , Mark K. Meyer
IPC分类号： F02C7/18 , F16L27/11 , F16L27/12
CPC分类号： F16L27/11 , F16L27/026
摘要： An expansion joint for connecting first and second fluid-carrying pipes comprising first and second annular couplings which are operably affixable to respective ones of the pipes. In a preferred embodiment the couplings include cylindrical bores of substantially the same diameter disposed relative to one another to form a passage for providing flow communication between the pipes. An annular bellows extends between the couplings for accommodating relative axial movement and angular misalignment between the pipes and is disposed radially outward of the passage to capture any fluid leaking between the interfacing surfaces of the couplings. A second cylindrical bore of a first one of the couplings engages an outer spherical surface of the second coupling to allow the second coupling to pivot in a manner which accommodates angular misalignment between the pipes. Means are provided for limiting the pivoting of the second coupling and for preventing the first coupling from rotating about a centerline of the joint, thereby avoiding unacceptable bending and torsional loading of the bellows. The expansion joint further includes means for limiting the axial compression and axial extension of the bellows.
摘要翻译：一种用于连接第一和第二流体输送管的膨胀接头，包括第一和第二环形联接器，其可操作地固定在相应的管道中。在优选实施例中，联接器包括相对于彼此设置的基本上相同直径的圆柱形孔，以形成用于在管之间提供流动连通的通道。环形波纹管在耦合器之间延伸，用于容纳管道之间的相对轴向运动和角度偏移，并且设置在通道的径向外侧，以捕获在联接器的接口表面之间泄漏的任何流体。联接器中的第一联接器的第二圆柱形孔接合第二联接器的外球面，以允许第二联接器以容纳管之间的角度偏移的方式枢转。提供了用于限制第二联接器的枢转并且用于防止第一联接件围绕接头的中心线旋转的装置，从而避免波纹管的不可接受的弯曲和扭转负载。膨胀接头还包括用于限制波纹管的轴向压缩和轴向延伸的装置。

3. 发明授权

US5127793A Turbine shroud clearance control assembly 失效
标题翻译：涡轮机清洁控制组件
公开(公告)号：US5127793A
公开(公告)日：1992-07-07
申请号：US531288
申请日：1990-05-31
申请人： Alan Walker , Thomas G. Wakeman , Dean T. Lenahan , Larry W. Plemmons , Andrew P. Elovic
发明人： Alan Walker , Thomas G. Wakeman , Dean T. Lenahan , Larry W. Plemmons , Andrew P. Elovic
IPC分类号： F01D11/10 , F01D11/08 , F01D25/24 , F02C7/00 , F02C7/20 , F02C7/28
CPC分类号： F01D25/246 , F01D11/08 , F05D2240/11
摘要： The clearances between an array of high pressure turbine blades and its surrounding high pressure turbine shroud as well as the clearances between an array of low pressure turbine blades and its associated low pressure turbine shroud are carefully controlled by a support structure which provides for evenly controlled circumferential cooling of the shroud support structure. Radial loads on the shroud support structure are reduced by counterbalancing loads imposed on the support structure by the shroud with predetermined pressure loads controlled and set through a series of cooling air cavities. The high pressure turbine shroud and low pressure turbine shroud are formed as integral segments in a segmented shroud design. Forward and aft shroud hanger members interconnect the shroud with its support so as to facilitate assembly and disassembly of the shroud segments to and from their support structure.
摘要翻译：高压涡轮机叶片阵列及其周围的高压涡轮机罩之间的间隙以及低压涡轮叶片阵列与其相关联的低压涡轮机罩之间的间隙由支撑结构小心地控制，所述支撑结构提供均匀控制的圆周护罩支撑结构的冷却。护罩支撑结构上的径向载荷通过由具有通过一系列冷却空气腔控制和设定的预定压力负载的护罩平衡负载施加在支撑结构上而减小。高压涡轮机护罩和低压涡轮机护罩在分段护罩设计中形成为整体段。前部和后部护罩悬挂构件将护罩与其支撑件互连，以便于护罩段与其支撑结构的组装和拆卸。

4. 发明授权

US4657484A Blade pitch varying means 失效
标题翻译：叶片间距变化手段
公开(公告)号：US4657484A
公开(公告)日：1987-04-14
申请号：US647283
申请日：1984-09-04
申请人： Thomas G. Wakeman , Neil Walker
发明人： Thomas G. Wakeman , Neil Walker
IPC分类号： B64C11/30 , B64C11/38 , B64C11/48
CPC分类号： B64C11/38 , B64C11/306 , B64D2027/005 , Y02T50/66
摘要： Blade pitch varying means for use in a gas turbine engine are disclosed. The blade pitch varying means may be used on an engine with a single row or two counterrotating rows of variable pitch blades which are disposed outwardly from an annular gas flowpath and which are connected with a rotating airfoil within the flowpath. The blade pitch varying means comprise actuation means, bearing means, and gearing means. The actuation means are in a nonrotating reference frame disposed inwardly from the flowpath and deliver an axial force. The bearing means transmit the axial force from the nonrotating into a rotating reference frame which contains both the propulsor blade and the airfoil in the gas flowpath. The gearing means are located in the rotating reference frame and convert the axial force into a force for varying the blade pitch.
摘要翻译：公开了一种用于燃气涡轮发动机的叶片间距变化装置。叶片桨距变化装置可以用于具有单排或两排可变桨距叶片的发动机，该排或两个可逆桨叶叶片从环形气体流路向外设置并且与流路内的旋转翼型件连接。叶片间距变化装置包括致动装置，轴承装置和传动装置。致动装置位于从流动路径向内设置并提供轴向力的非旋转基准框架中。轴承装置将来自非旋转的轴向力传递到在气体流动路径中包含推进器叶片和翼型的旋转参考框架。传动装置位于旋转的参考系中，并将轴向力转换成用于改变叶片间距的力。

5. 发明授权

US4555901A Combustion chamber construction 失效
标题翻译：燃烧室施工
公开(公告)号：US4555901A
公开(公告)日：1985-12-03
申请号：US316532
申请日：1972-12-19
申请人： Thomas G. Wakeman , Harvey M. Maclin
发明人： Thomas G. Wakeman , Harvey M. Maclin
IPC分类号： F23R3/00 , F23R3/08 , F02C7/20
CPC分类号： F23R3/08 , F23R3/002 , F05B2230/70 , F05B2230/80
摘要： A combustion chamber for use in gas turbine engines is provided with a liner formed of a high temperature material. The liner includes a plurality of panels of material mounted by means of a slideable, frictional mounting arrangement upon a high strength structural frame. As a result of this mounting arrangement, the liner is substantially isolated from structural forces associated with the combustion chamber, while the frame is substantially isolated from thermal stresses associated with the liner. Means are provided for positioning and securing individual panel members axially relative to the frame. The panels may be continuous annular bodies, or may be circumferentially segmented. In the latter case, means are provided for mounting individual panels in a slideable, frictional cooperation with laterally adjacent panels, as well as for sealing the abutting junctions. The individual liner panels may be easily removed for repair or replacement without disassembling the frame and associated components.
摘要翻译：用于燃气涡轮发动机的燃烧室设置有由高温材料形成的衬套。衬套包括通过可滑动的摩擦安装装置安装在高强度结构框架上的多个材料面板。作为这种安装结构的结果，衬套基本上与与燃烧室相关联的结构力隔离，而框架基本上与衬套相关联的热应力隔离。提供了用于相对于框架轴向地定位和固定单个面板构件的装置。面板可以是连续的环形体，或者可以是圆周分段的。在后一种情况下，提供了用于将单独的面板安装在与横向相邻的面板可滑动，摩擦协作以及用于密封邻接结的装置。单独的衬板可以容易地移除用于修理或更换，而不拆卸框架和相关组件。

6. 发明授权

US4187675A Compact air-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空气 - 空气热交换器
公开(公告)号：US4187675A
公开(公告)日：1980-02-12
申请号：US842139
申请日：1977-10-14
申请人： Thomas G. Wakeman
发明人： Thomas G. Wakeman
IPC分类号： F02C7/18 , F28D21/00
CPC分类号： F02C7/185 , F28D21/0014 , F28D2021/0021 , Y02T50/675
摘要： A structurally compact air-to-air heat exchanger, for a gas turbine engine of the fan bypass type, 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. This goal is achieved, in part, by using a portion of the cool flow of fan air as a heat sink, without disturbing the flow of the fan air stream. The heat exchanger is disposed internal of the engine, and, it includes a plurality of flow tubes through which flows the hot cooling air, with the flow tubes positioned in a crossflow relationship with and to a portion of the cool flow of fan air. Three (3) variations of the preferred embodiment of the heat exchanger also are taught.
摘要翻译：用于风扇旁路式燃气涡轮发动机的结构紧凑的空气 - 空气热交换器，其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热涡轮机及其部件，的发动机。该目标部分地通过使用一部分冷却风扇的风扇作为散热器，而不会干扰风扇空气流的流动。热交换器设置在发动机的内部，并且其包括多个流管，流动管通过该多个流管与流动的管道以与风扇空气的冷却流的一部分交叉流动的关系流动。还教导了热交换器的优选实施例的三（3）变型。

7. 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。

8. 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。

9. 发明授权

US5224831A Fan blade protection system 失效
标题翻译：风扇叶片保护系统
公开(公告)号：US5224831A
公开(公告)日：1993-07-06
申请号：US877351
申请日：1992-04-30
申请人： Thomas C. Hermans , Thomas G. Wakeman , Ambrose A. Hauser
发明人： Thomas C. Hermans , Thomas G. Wakeman , Ambrose A. Hauser
IPC分类号： B64C11/02 , F01D5/30 , F01D21/04
CPC分类号： F01D21/045 , B64C11/06 , B64C11/306 , F01D5/30 , B64D2027/005 , F05D2220/324 , Y02T50/66
摘要： In one type of aircraft propulsion system, propeller blades are mounted on a ring which surrounds a turbine. An annular space exists between the turbine and the ring. If a propeller blade should break free, the unbalanced centrifugal load tends to deform the ring. The invention reduces the deformation, as by locating spacers between the turbine and the ring.
摘要翻译：在一种类型的飞行器推进系统中，螺旋桨叶片安装在环绕涡轮机的环上。在涡轮和环之间存在环形空间。如果螺旋桨叶片脱落，离心力不平衡会使环变形。本发明通过在涡轮机和环之间定位隔板来减少变形。

10. 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.

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