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51. 发明申请

US20160076383A1 FILM COOLED ARTICLE 审中-公开
标题翻译：电影冷却文章
公开(公告)号：US20160076383A1
公开(公告)日：2016-03-17
申请号：US14856512
申请日：2015-09-16
申请人： United Technologies Corporation
发明人： Brandon W. Spangler , Jesse M. Carr , Bryan P. Dube , Yongxiang D. Xue
IPC分类号： F01D5/18 , F01D25/12 , F23R3/00 , F02C7/24 , F23R3/06 , F01D11/08 , F02C7/18
CPC分类号： F01D5/186 , F01D9/065 , F01D11/08 , F01D25/12 , F02C7/18 , F02C7/24 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/14 , F05D2260/202 , F05D2300/16 , F05D2300/20 , F05D2300/6033 , F23R3/002 , F23R3/06 , Y02T50/672 , Y02T50/676
摘要： A film cooled component includes multiple film cooling holes. At least one of the film cooling holes has an elliptical cross sectional opening along the exterior surface of the film cooled component.
摘要翻译：膜冷却部件包括多个膜冷却孔。薄膜冷却孔中的至少一个具有沿着薄膜冷却部件的外表面的椭圆形横截面开口。

52. 发明申请

US20160069192A1 DOUBLE-JET FILM COOLING STRUCTURE AND METHOD FOR MANUFACTURING SAME 有权
标题翻译：双盖冷却结构及其制造方法
公开(公告)号：US20160069192A1
公开(公告)日：2016-03-10
申请号：US14944503
申请日：2015-11-18
申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA , B&B AGEMA GmbH
发明人： Ryozo TANAKA , Takao SUGIMOTO , Masahide KAZARI , Tomoki TANIGUCHI , Karsten KUSTERER , Dieter BOHN , Nurettin TEKIN
IPC分类号： F01D5/18 , B23H1/04
CPC分类号： F01D5/186 , B23H1/04 , B23H9/10 , B23H9/14 , F01D9/065 , F05D2230/12 , F05D2240/11 , F05D2240/81 , F05D2250/14 , F05D2250/231 , F05D2250/75 , F05D2260/202 , F23R3/06 , F23R2900/03042
摘要： A double-jet film cooling structure includes: an injection port, formed on a wall surface facing a high-temperature gas passage; a main passage as a straight round hole to supply cooling medium to the injection port; a pair of branch passages as straight round holes; and communication passages connecting the main passage to the branch passages. The main passage and the branch passages have same constant inner diameters. Each communication passages has an envelope surface obtained by continuously arranging straight round holes each passing a branch point and having the constant inner diameter. Transverse injection angles of the branch passages relative to gas flow along the wall surface are oriented in opposite directions. An angle between axial direction of the main passage and the wall surface is greater than an angle formed between axial direction of branch passage and the wall surface.
摘要翻译：双喷射薄膜冷却结构包括：形成在面向高温气体通道的壁面上的喷射口; 主通道作为直的圆孔向冷却介质供给喷射口; 一对分支通道为直圆孔; 以及将主通道连接到分支通道的连通通道。主通道和分支通道具有相同的恒定内径。每个连通通道具有通过连续地布置通过分支点并具有恒定内径的直圆孔而获得的包络面。分支通道相对于沿着壁表面的气流的横向喷射角度被定向在相反的方向。主通道的轴向与壁面之间的角度大于在分支通道的轴向方向和壁面之间形成的角度。

53. 发明授权

US09249673B2 Turbine rotor blade platform cooling 有权
标题翻译：涡轮转子叶片平台冷却
公开(公告)号：US09249673B2
公开(公告)日：2016-02-02
申请号：US13341018
申请日：2011-12-30
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A platform cooling arrangement for a turbine rotor blade having a platform at an interface between an airfoil and a root, the root including attachment means and a shank, wherein the platform comprises a suction side that includes a topside extending from an airfoil base to a suction side slashface, and wherein the platform overhangs a shank cavity. The platform cooling arrangement may include: a pocket formed in an underside region of the platform, the pocket comprising a mouth that fluidly communicates with the shank cavity; a manifold extending from the suction side slashface to a pressure side slashface, the manifold including a connection to the pocket; and cooling apertures that extend from connections made with the pocket and manifold to ports.
摘要翻译：一种用于涡轮转子叶片的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，所述根部包括附接装置和柄部，其中所述平台包括吸力侧，所述吸力侧包括从翼型基部到吸力侧斜面，并且其中所述平台突出于柄空腔。平台冷却装置可以包括：形成在平台的下侧区域中的口袋，所述口袋包括与所述柄腔流体连通的口; 歧管从吸力侧斜面延伸到压力侧斜面，歧管包括与口袋的连接; 以及从由袋和歧管制成的连接件延伸到端口的冷却孔。

54. 发明授权

US09243503B2 Components with microchannel cooled platforms and fillets and methods of manufacture 有权
标题翻译：具有微通道冷却平台和圆角的部件和制造方法
公开(公告)号：US09243503B2
公开(公告)日：2016-01-26
申请号：US13478517
申请日：2012-05-23
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F01D5/18 , F01D5/28
CPC分类号： F01D5/187 , F01D5/288 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A component includes a substrate that has outer and inner surfaces. The inner surface defines at least one hollow, interior space. The outer surface defines pressure and suction sidewalls that are joined together at leading and trailing edges of the component and together form an airfoil portion of the component. The outer substrate surface further defines at least one platform and at least one fillet that extends between and integrally connects the airfoil to the respective platform. The outer surface defines one or more grooves that extend at least partially along a respective fillet. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface and including at least a structural coating that extends over the groove(s). The groove(s) and the structural coating together define channel(s) for cooling the respective fillet.
摘要翻译：组件包括具有外表面和内表面的基底。内表面限定至少一个中空的内部空间。外表面限定压力和抽吸侧壁，其在部件的前缘和后缘处连接在一起并且一起形成部件的翼型部分。外基材表面进一步限定至少一个平台和至少一个在所述翼型件之间延伸并且将翼片整体连接到相应的平台的圆角。外表面限定了至少部分地沿着相应的圆角延伸的一个或多个凹槽。每个槽与相应的中空的内部空间流体连通。该部件还包括设置在外部基底表面的至少一部分上的涂层，并且至少包括在凹槽上延伸的结构涂层。沟槽和结构涂层一起限定用于冷却相应圆角的通道。

55. 发明授权

US09243500B2 Turbine blade platform with U-channel cooling holes 有权
标题翻译：涡轮叶片平台配有U形通道冷却孔
公开(公告)号：US09243500B2
公开(公告)日：2016-01-26
申请号：US13537258
申请日：2012-06-29
申请人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
发明人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
IPC分类号： F01D5/18 , F01D5/08
CPC分类号： F01D5/085 , F01D5/081 , F01D5/18 , F05D2240/81 , Y02T50/676
摘要： A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.
摘要翻译：用于燃气涡轮发动机的涡轮机叶片包括一个翼型件，其包括通过间隔开的压力和吸力侧面连接的前缘和后缘，以提供在径向方向上延伸的外部翼面。后缘设置在涡轮叶片的后侧。根部支撑翼型件延伸的平台，并且冷却通道在根部内在径向方向上延伸到翼型件。下翼设置在平台的后侧，在轴向方向上延伸，以提供具有沿圆周方向延伸的平台的U形通道。冲击孔从U形通道延伸到冷却通道。

56. 发明申请

US20160010467A1 GAS TURBINE ENGINE COMPONENT COOLING CHANNELS 审中-公开
标题翻译：气体涡轮发动机组件冷却通道
公开(公告)号：US20160010467A1
公开(公告)日：2016-01-14
申请号：US14772215
申请日：2014-03-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Scott H. LAMSON , Andrew D. MILLIKEN
IPC分类号： F01D5/18 , F01D25/30 , F01D11/08 , F02C7/18 , F02C7/25 , F01D9/04 , F01D25/12
CPC分类号： F01D5/187 , F01D5/186 , F01D9/041 , F01D9/065 , F01D11/08 , F01D25/12 , F01D25/30 , F02C7/18 , F02C7/25 , F05D2220/32 , F05D2240/11 , F05D2240/127 , F05D2240/35 , F05D2240/81 , F05D2250/15 , F05D2250/25 , F05D2260/20 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R2900/03042
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a wall, a first channel extending at least partially through the wall to a first outlet, and a second channel adjacent to the first channel and extending to a second outlet. The first channel is configured to communicate a cooling fluid along a first swirl flow path and the second channel is configured to communicate the cooling fluid along a second swirl flow path that is opposite the first swirl flow path.
摘要翻译：根据本公开的示例性方面的部件包括壁，至少部分地穿过壁延伸到第一出口的第一通道和邻近第一通道的第二通道并且延伸到第二出口。第一通道被配置成沿着第一旋流流动通道传送冷却流体，并且第二通道构造成沿着与第一旋流流动路径相对的第二旋流流路连通冷却流体。

57. 发明申请

US20150377032A1 GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING 审中-公开
标题翻译：燃气涡轮发动机组件与组合的油面和平台冷却
公开(公告)号：US20150377032A1
公开(公告)日：2015-12-31
申请号：US14766190
申请日：2014-02-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Scott D. LEWIS , Brandon M. RAPP , Jeffrey S. BEATTIE , Matthew Andrew HOUGH , Bret M. TELLER , Jeffrey Michael JACQUES , Max ASTERLIN
IPC分类号： F01D5/18 , F23R3/02 , F01D9/02
CPC分类号： F01D5/186 , F01D5/18 , F01D9/023 , F01D9/065 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间轴向延伸的平台，在第一配合面和第二配合面之间周向延伸，以及包括气体通道表面和非气体通道表面。该部件限定至少一个至少部分地在部件内部延伸的空腔。第一多个冷却孔从所述至少一个空腔延伸到所述第一配合面和所述第二配合面中的至少一个，并且第二多个冷却孔从所述至少一个空腔或所述非气体通道表面延伸到气路面。

58. 发明申请

US20150369072A1 SPLIT AIRFOIL CLUSTER AND METHOD THEREFOR 审中-公开
标题翻译：分离空中飞行器集群及其方法
公开(公告)号：US20150369072A1
公开(公告)日：2015-12-24
申请号：US14766477
申请日：2014-02-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Edward R. BAREISS , Russell J. BERGMAN , Bradley T. DUELM , Michael L. MILLER , Paul M. PELLET
IPC分类号： F01D9/04 , B23K28/00 , B23H9/14 , B23K1/00 , F01D25/12 , B23K26/382
CPC分类号： F01D9/041 , B23H9/14 , B23K1/00 , B23K1/0018 , B23K26/382 , B23K28/00 , B23K2101/001 , F01D5/005 , F01D5/186 , F01D5/187 , F01D9/044 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/14 , F05D2230/236 , F05D2230/30 , F05D2230/64 , F05D2240/81 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A method of fabricating airfoil cluster includes providing an airfoil cluster that has a pair of spaced-apart airfoils that extend from a common platform wall. The airfoil cluster is then divided through the common platform wall to provide separate first and second airfoil segments. At least one cooling hole is then formed in at least one of the first and second airfoil segments. The segments are then metallurgically fused together in a distinct metallurgical joint in the common platform wall.
摘要翻译：一种制造翼型组的方法包括提供一翼型组，其具有从公共平台壁延伸的一对间隔开的翼型。然后将翼型组通过公共平台壁分开，以提供单独的第一和第二翼型段。然后在第一和第二翼型段中的至少一个中形成至少一个冷却孔。然后将这些片段在公共平台壁中的不同冶金接头中冶金熔合在一起。

59. 发明申请

US20150361814A1 GAS TURBINE ROTOR BLADE AND GAS TURBINE ROTOR 有权
标题翻译：气体涡轮转子叶片和气体涡轮转子
公开(公告)号：US20150361814A1
公开(公告)日：2015-12-17
申请号：US14763727
申请日：2014-01-14
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Richard Bluck , David Butler , Jonathan Mugglestone , David Overton
IPC分类号： F01D11/00 , F01D5/14 , F01D5/02
CPC分类号： F01D11/008 , F01D5/02 , F01D5/147 , F01D11/006 , F05D2220/32 , F05D2240/55 , F05D2240/57 , F05D2240/80 , F05D2240/81 , F05D2250/294 , Y10T29/49323
摘要： A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove.
摘要翻译：燃气轮机转子和叶片包括沿着转子叶片的跨度方向布置的根部，平台和翼型部分，位于根部和翼型部分之间的平台。该平台具有上游侧和下游侧，从上游侧向下游侧延伸的侧面，每侧面的轴向凹槽垂直于跨距方向延伸，在跨度方向上延伸小部分。每个侧面中的径向凹槽朝向轴向凹槽延伸，其跨度方向上延伸的部件和垂直于跨度方向的延伸部分。径向槽具有远离轴向槽的第一端和向轴向槽显示的第二端。第二端距轴向槽的距离在第二端和轴向槽之间形成无沟槽部分。

60. 发明授权

US09175565B2 Systems and apparatus relating to seals for turbine engines 有权
标题翻译：与涡轮发动机密封相关的系统和设备
公开(公告)号：US09175565B2
公开(公告)日：2015-11-03
申请号：US13566189
申请日：2012-08-03
申请人： Christopher Donald Porter , Gary Michael Itzel
发明人： Christopher Donald Porter , Gary Michael Itzel
IPC分类号： F01D5/08 , F01D11/00 , F01D11/04
CPC分类号： F01D5/081 , F01D11/001 , F01D11/04 , F05D2240/55 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A seal in a turbine of a combustion turbine engine is described. The seal is formed within a trench cavity defined between a rotor blade and a stator blade. The stator blade includes a sidewall projection and the rotor blade includes an angel wing projection extending toward the stator blade. The side wall projection overhangs the angel wing projection. The seal include: a port disposed on an inboard surface of the stator projection; and deflecting structure disposed on the angel wing projection. The deflecting structure may be configured to receive the fluid expelled from the port and deflect the fluid toward an inlet of the trench cavity.
摘要翻译：描述了燃气涡轮发动机的涡轮机中的密封件。密封件形成在限定在转子叶片和定子叶片之间的沟槽腔内。定子叶片包括侧壁突起，转子叶片包括向定子叶片延伸的天使翼突起。侧壁突起悬挂天使翼投影。密封件包括：设置在定子突起的内表面上的端口; 以及设置在天使翼突起上的偏转结构。偏转结构可以被配置为接收从端口排出的流体并使流体朝向沟槽腔的入口偏转。

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