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公开(公告)号：US5328331A
公开(公告)日：1994-07-12
申请号：US82114
申请日：1993-06-28
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/10 , F05D2260/201 , F05D2260/2212
摘要： A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with an integrally formed double shell outer wall surrounding at least one radially extending cavity. The inner and the outer shells are integrally formed of the same material together with tying elements which space apart the shells and mechanically and thermally tie the shells together. The present invention contemplates tying elements including pedestals, rods, and/or continuous or intermittent ribs. Impingement cooling means for the outer shell, in the form of impingement cooling holes, is provided on the inner shell to direct the coolant in impingement jet arrays against the outer shell, thereby, cooling the outer shell.
摘要翻译： 用于燃气涡轮发动机部件如涡轮叶片或叶片的可冷却翼型设置有围绕至少一个径向延伸腔的整体形成的双壳外壁。 内壳和外壳由相同的材料一起形成，并与隔离空间的捆绑元件一体地形成，并将壳体机械地和热结合在一起。 本发明考虑了包括基座，杆和/或连续或间歇肋的元件的捆扎。 在内壳上设置用于外壳形式的冲击冷却孔的冲击冷却装置，以将冲击喷射阵列中的冷却剂引导到外壳上，由此冷却外壳。
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公开(公告)号：US5269133A
公开(公告)日：1993-12-14
申请号：US979362
申请日：1992-11-20
申请人： Thomas T. Wallace
发明人： Thomas T. Wallace
CPC分类号： F02K3/02 , F02C7/185 , F28D7/12 , F28D2021/0026 , Y02T50/67 , Y02T50/672 , Y02T50/675
摘要： A heat exchanger for cooling turbine components of a gas turbofan engine in which air to be cooled is directed along a first annular, radially extending path away from the engine and cooled by bypass air. The cooled air is returned to the engine along a second radially-extending path concentric to the first path. In a preferred embodiment, the heat exchanger is a standpipe extending from the compressor outlet to the bypass air duct and includes inner and outer tubular members oriented concentrically to form inner and outer counterflowing air flow paths which also are concentrically arranged. The outer member is mounted on the combustor casing and the inner member on a diffuser within the casing. Accordingly, no mechanical connection exists between the inner and outer members.
摘要翻译： 一种用于冷却气体涡轮风扇发动机的涡轮机部件的热交换器，其中待冷却的空气沿着远离发动机的第一环形径向延伸的路径引导并由旁路空气冷却。 冷却的空气沿着与第一路径同心的第二径向延伸路径返回到发动机。 在优选实施例中，热交换器是从压缩机出口延伸到旁路空气管道的立管，并且包括同心取向的内部和外部管状构件，以形成同心布置的内部和外部逆流空气流动路径。 外部构件安装在燃烧器壳体上，内部构件安装在壳体内的扩散器上。 因此，内部和外部构件之间不存在机械连接。
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公开(公告)号：US5941537A
公开(公告)日：1999-08-24
申请号：US923916
申请日：1997-09-05
CPC分类号： F01D5/148 , F01D11/00 , F01D17/162 , F16J15/164 , Y02T50/671 , Y02T50/673
摘要： A static seal includes first and second spaced apart walls having a gap therebetween for channeling a pressurized fluid. The first wall includes a recessed seat facing the second wall defined by spaced apart first and second faces joined together at a base. A seal insert is loosely disposed in the seat and is trapped therein by the first and second faces. The first and second faces are shorter than the insert to project a top of the insert above the seat and below the second wall for initially promoting flow of the fluid over the insert top to deploy the insert in abutting contact with both the second face and the second wall to seal the gap.
摘要翻译： 静态密封件包括第一和第二隔开的壁，其间具有用于引导加压流体的间隙。 所述第一壁包括面向所述第二壁的凹入座，所述第二壁由在基部处连接在一起的间隔开的第一和第二面限定。 密封插入件松散地设置在座中并被第一和第二面捕获在其中。 第一和第二表面比插入件短，以在座椅的上方突出并在第二壁下方突出插入件的顶部，用于最初促进流体流过插入物顶部，以将插入件与第二面和第二面邻接接触 第二墙密封缝隙。
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公开(公告)号：US5931636A
公开(公告)日：1999-08-03
申请号：US919520
申请日：1997-08-28
申请人： Joseph W. Savage , Ely E. Halila , Robert J. Orlando , Valentine R. Boehm, Jr. , James A. Martus , Thomas T. Wallace , Monty L. Shelton
发明人： Joseph W. Savage , Ely E. Halila , Robert J. Orlando , Valentine R. Boehm, Jr. , James A. Martus , Thomas T. Wallace , Monty L. Shelton
CPC分类号： F01D17/141 , F01D17/162 , F01D17/167
摘要： A variable area turbine nozzle includes a plurality of circumferentially adjoining nozzle segments. Each nozzle segment includes outer and inner bands, with a plurality of first vane segments fixedly joined therebetween. A plurality of second vane segments adjoin respective ones of the first vane segments to define therewith corresponding vanes which are spaced apart to define respective throats of minimum flow area for channeling therethrough combustion gas. The second vane segments are pivotable to selectively vary the throat area.
摘要翻译： 可变区域涡轮喷嘴包括多个周向邻接的喷嘴段。 每个喷嘴段包括外带和内带，其间固定有多个第一叶片段。 多个第二叶片段邻接相应的第一叶片段，以与其相对应地限定相应的叶片，其间隔开以限定用于引导燃烧气体的最小流动面积的相应喉部。 第二叶片段可枢转以选择性地改变喉部区域。
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公开(公告)号：US5281097A
公开(公告)日：1994-01-25
申请号：US979026
申请日：1992-11-20
CPC分类号： F01D11/006 , F01D5/081 , F01D5/22 , F05D2240/81 , Y02T50/676 , Y10S416/50
摘要： Sheet Metal thermal control dampers are disposed in the cavities between turbine blades to bear against the undersides of opposed blade platforms portions of angularly adjacent blades under centrifugal loading to dampen blade vibrations and to seal the gaps between platforms against the radial flow of working fluid into the interblade cavities. The dampers are configured to cooperate with forward and aft seals to also block the axial flow of working fluid through the interblade cavities. Holes are provided in the dampers through which cooling air introduced into the interblade cavities can flow into contact with the platform undersides and cool the platforms, thereby controlling temperature rise in the blade attachment structure.
摘要翻译： 钣金热控制阻尼器设置在涡轮机叶片之间的空腔中，以在离心负载下抵靠角度相邻叶片的相对的叶片平台部分的下侧，以抑制叶片振动并且将平台之间的间隙抵抗工作流体的径向流动进入 interblade腔。 阻尼器构造成与前后密封件配合以阻止工作流体通过叶片间隙的轴向流动。 在阻尼器中设置有孔，通过该阻尼器将引入到叶片间空腔中的冷却空气流动到与平台下侧接触并冷却平台，从而控制叶片附接结构中的温度升高。
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