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1.发明授权Apparatus for removably attaching a core frame to a vane frame with a stable mid ring 失效用于将芯框架可拆卸地连接到具有稳定中环的叶片框架的装置
公开(公告)号：US5222360A
公开(公告)日：1993-06-29
申请号：US785365
申请日：1991-10-30
申请人： Eugene J. Antuna , Donald F. Keck , Robert H. Roth , James W. Brantley , Thomas G. Wakeman , Jeffrey B. Fravel , Alan B. Corbeil , William J. Strock
发明人： Eugene J. Antuna , Donald F. Keck , Robert H. Roth , James W. Brantley , Thomas G. Wakeman , Jeffrey B. Fravel , Alan B. Corbeil , William J. Strock
CPC分类号： B64D27/18 , B64D27/26 , F02C7/20 , Y02T50/672
摘要： A gas turbine engine has a core frame separable from a vane frame for removably attaching the vane frame to a core structure through a mid ring. The mid ring includes an annular forward panel and an annular aft panel, each of which has a radially outer flange and a radially inner flange. The inner flanges are welded to the core frame and the outer flanges are bolted to the vane frame. A plurality of circumferentially spaced stiffeners extend between the forward and aft panels, with each of the stiffeners including a pair of stringers extending diagonally across the stiffeners. Panels may be incorporated with the stringers between the triangular shaped areas adjacent the forward and aft panels of the stiffener. The bolted connection between the mid ring and the vane frame includes a plurality of tongue and groove joints formed in the flanges of the mid ring and vane frame. The tongue and groove joints provide additional radial support for the core engine within the vane frame. Preferably, the tongue and groove joints are formed with angular sides so that conformance between the joints can be achieved by simply tightening the bolts attaching the joints. In one embodiment, the tongue and groove joints may only be used at preselected circumferential positions with the remainder of the flange connections using overlapping lap joints.
摘要翻译： 燃气涡轮发动机具有与叶片框架分离的芯框架，用于通过中环将叶片框架可拆卸地附接到芯结构。 中环包括环形前板和环形后板，每个板具有径向外凸缘和径向内凸缘。 内部凸缘焊接到芯框架，外部凸缘螺栓连接到叶片框架。 多个周向隔开的加强件在前板和后板之间延伸，其中每个加强件包括一对沿着加强件对角延伸的纵梁。 面板可以与邻近加强筋的前板和后板的三角形形状区域之间的桁条结合。 中间环和叶片框架之间的螺栓连接包括形成在中环和叶片框架的凸缘中的多个榫舌和凹槽接头。 舌和槽接头为叶片框架内的核心发动机提供额外的径向支撑。 优选地，舌和沟槽接头形成有角侧，使得可以通过简单地紧固附接接头的螺栓来实现接头之间的一致性。 在一个实施例中，舌和槽接头可以仅在预选的圆周位置处使用，其余的凸缘连接使用重叠搭接接头。
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公开(公告)号：US4863352A
公开(公告)日：1989-09-05
申请号：US667663
申请日：1984-11-02
CPC分类号： F16C19/56 , B64C11/06 , F01D5/02 , B64D2027/026 , Y02T50/671
摘要： Blade carrying means for variable pitch propulsor blades of a gas turbine engine are disclosed. The blade carrying means comprise dual, axially positioned rings and a plurality of generally cylindrical bearing journals supported between the rings. Each of the journals has a radially outer and inner edge and is adapted to support a single propulsor blade. The blade carrying means also comprise stiffening means, such as a bulkhead attached to the inner edge, for preventing distortion of the journal inner edge.
摘要翻译： 公开了一种用于燃气涡轮发动机的变桨距推进叶片的叶片承载装置。 刀片承载装置包括双轴向定位的环和支撑在环之间的多个大致圆柱形的轴承轴颈。 每个轴颈具有径向外部和内部边缘，并且适于支撑单个推进器叶片。 叶片承载装置还包括加强装置，例如附接到内边缘的隔板，用于防止轴颈内边缘的变形。
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公开(公告)号：US5112191A
公开(公告)日：1992-05-12
申请号：US336375
申请日：1989-04-11
CPC分类号： B64C11/06 , B64D29/00 , B64D2027/026 , Y02T50/66
摘要： The invention concerns a cowling for aircraft propulsion systems of the counterrotating propeller type. The cowling includes a pair of mounting rings located fore and aft of a propeller array. Removable panels extend between the mounting rings and contain openings through which the propeller blades extend.
摘要翻译： 本发明涉及用于逆转螺旋桨型飞机推进系统的整流罩。 整流罩包括位于螺旋桨阵列前后的一对安装环。 可移动面板在安装环之间延伸并包含螺旋桨叶片延伸通过的开口。
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公开(公告)号：US5385013A
公开(公告)日：1995-01-31
申请号：US159917
申请日：1993-11-30
CPC分类号： F02C7/20 , F01D25/14 , Y02T50/672 , Y02T50/675
摘要： A gas turbine engine thermal backbone deflection control apparatus to counter the effects of backbone bending due to nacelle aerodynamic, thrust, and maneuver loads by introducing a controlled backbone counter-bending moment by applying an uneven temperature or thermal field around the backbone to induce controlled compression and/or tensioning forces in the backbone or casing between axially spaced apart frames connected by the backbone. One embodiment of the invention provides for flowing thermal control air along an axially and circumferentially sector of the engine casing. The thermal backbone deflection control apparatus is controlled by the engines digital electronic control system using input signals generated by engine thrust load, inlet moment load sensors and/or blade tip clearance sensors.
摘要翻译： 一种燃气涡轮发动机热骨干偏转控制装置，通过在骨架周围施加不均匀的温度或热场引入受控骨架反弯矩来抵消由于机舱空气动力学，推力和机动负载引起的主干弯曲的影响，以引起受控压缩 和/或骨架或壳体中由骨架连接的轴向隔开的框架之间的张紧力。 本发明的一个实施例提供沿着发动机壳体的轴向和周向扇区流动的热控制空气。 热骨干偏转控制装置由引擎数字电子控制系统使用由发动机推力负载，入口力矩负载传感器和/或叶片顶端间隙传感器产生的输入信号来控制。
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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
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。
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公开(公告)号：US5127793A
公开(公告)日：1992-07-07
申请号：US531288
申请日：1990-05-31
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。
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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
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。
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公开(公告)号：US4555901A
公开(公告)日：1985-12-03
申请号：US316532
申请日：1972-12-19
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。
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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
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。
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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
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。
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