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1. 发明公开

EP2787174A3 Gas turbine engines with turbine airfoil cooling 有权转让
标题翻译：涡轮机翼型冷却的燃气涡轮发动机
公开(公告)号：EP2787174A3
公开(公告)日：2018-03-07
申请号：EP14161162.4
申请日：2014-03-21
申请人： Honeywell International Inc.
发明人： Crites Daniel Cregg , Morris, Mark C. , Crosatti, Lorenzo , Riahi, Ardeshir
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： An airfoil (310) for a gas turbine engine is provided. The airfoil includes a body (311) with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall (402) disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber (424) and a leading edge chamber (422). The interior wall defines a cooling hole (450) with a base portion (470) and a locally extended portion (480) to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
摘要翻译：提供了用于燃气涡轮发动机的翼型件（310）。翼型件包括具有前缘，后缘，在前缘和后缘之间延伸的第一侧壁以及在前缘和后缘之间延伸的第二侧壁的主体（311）。身体确定了一个内腔。翼型件包括布置在本体的内部空腔内并且在第一壁和第二壁之间延伸以限定供应室（424）和前缘室（422）的内壁（402）。内壁限定具有底座部分（470）和局部延伸部分（480）的冷却孔（450），以将冷却空气从供应室引导至前缘室，使得冷却空气冲击前缘。

2. 发明公开

EP2733308A3 Turbine engines with ceramic vanes and methods for manufacturing the same 有权转让
标题翻译：具有陶瓷叶片的涡轮发动机及其制造方法
公开(公告)号：EP2733308A3
公开(公告)日：2017-06-21
申请号：EP13183825.2
申请日：2013-09-10
申请人： Honeywell International Inc.
发明人： Zurmehly, George E. , Ortiz, Milton , Poon, Kin , Vinup, Michael , Riahi, Ardeshir
IPC分类号： F01D5/14 , F01D5/28
CPC分类号： F01D5/12 , F01D5/147 , F01D5/284 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/49316
摘要： A vane assembly includes first and second annular metal rings (31,48) configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion (38). The assembly further includes a ceramic matrix composite vane (30) configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member (33) disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.
摘要翻译：叶片组件包括第一和第二环形金属环（31,48），所述第一和第二环形金属环构造成在其间接收压缩气流。第一和第二环形圈每个包括切口部分（38）。该组件还包括陶瓷基质复合叶片（30），其构造为翼型，其具有钝的圆形鼻部和扁平且渐缩的尾部。叶片的第一径向端部刚性地设置在第一环形圈上，叶片的第二径向端部可滑动地设置在第二环形圈的切口部分内，使得叶片由第一和第二环形圈包围。叶片包括径向贯穿的中空通孔部分。更进一步地，该组件包括金属细长构件（33），该金属细长构件设置在叶片的中空部分内并且延伸穿过叶片的中空部分并穿过第一环形圈的切口部分。

3. 发明公开

EP2071126A3 Turbine blades and methods of manufacturing 有权转让
标题翻译：涡轮机叶片及其制造方法的涡轮叶片
公开(公告)号：EP2071126A3
公开(公告)日：2013-09-18
申请号：EP08165957.5
申请日：2008-10-06
申请人： Honeywell International Inc.
发明人： Riahi, Ardeshir , Poon, Kin , Chou, David , Malak, Malak F.
IPC分类号： F01D5/14 , F01D5/20
CPC分类号： F01D5/147 , F01D5/18 , F01D5/20 , F05D2230/10 , F05D2230/211 , F05D2240/307 , Y02T50/676
摘要： A turbine blade (100) includes a convex suction side wall (112), a concave pressure side wall (110), a tip wall (114), an internal cooling circuit (146), and a plurality of tip edge channels (144). The tip wall (114) is recessed from a first tip edge (130) of the suction side wall (112) and a second tip edge (132) of the concave pressure side wall (110) to define a suction side wall tip section (138) and a pressure side wall tip section (140), and the suction side wall tip section (138) is shorter than the pressure side wall tip section (140). The internal cooling circuit (146) is formed at least partially between the convex suction side wall (112), the concave pressure side wall (110), and the tip wall (114). The plurality of tip edge channels (144) formed through the first tip edge (130) of the convex suction side wall (112) extend to the internal cooling circuit (146). Methods of manufacturing turbine blades (100) are also provided.

4. 发明公开

EP2463479A2 Turbine rotor disks and turbine assemblies 审中-公开
标题翻译： Turbinenrotorscheiben und Turbinenanordnungen
公开(公告)号：EP2463479A2
公开(公告)日：2012-06-13
申请号：EP11192909.7
申请日：2011-12-09
申请人： Honeywell International Inc.
发明人： Halfmann, Steve , Crites, Daniel Cregg , Malak, Malek Fouad , Morris, Mark C. , Riahi, Ardeshir , Wakefield, Brandan
IPC分类号： F01D5/08
CPC分类号： F01D5/085 , F01D5/088 , F01D5/3007 , F05D2240/81 , Y02T50/676
摘要： A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface.
摘要翻译：提供涡轮转子盘。涡轮转子盘包括轮毂，附接到毂的环，环包括径向向外延伸并围绕环的圆周设置的多个柱，每个柱包括第一径向延伸面，第二径向延伸面以及在所述第一和第二径向延伸面之间轴向延伸的刀片附接表面，形成在每个柱中并从所述第一径向延伸面朝向所述第二径向延伸面延伸的主冷却空气供给通道，以及多个辅助在每个柱中形成并且从主冷却空气供给通道延伸到叶片附接表面的喷射开口。

5. 发明授权

EP2787174B1 Gas turbine engines with turbine airfoil cooling 有权转让
公开(公告)号：EP2787174B1
公开(公告)日：2019-07-03
申请号：EP14161162.4
申请日：2014-03-21
申请人： Honeywell International Inc.
发明人： Crites Daniel Cregg , Morris, Mark C. , Crosatti, Lorenzo , Riahi, Ardeshir
IPC分类号： F01D5/18

6. 发明公开

EP2653652A3 Axially-split radial turbine 有权转让
标题翻译：轴向分体式径流式涡轮机
公开(公告)号：EP2653652A3
公开(公告)日：2018-04-04
申请号：EP13162820.8
申请日：2013-04-08
申请人： Honeywell International Inc.
发明人： Jan, David K. , Zollars, Christopher , Rana, Rajiv , Polakis, Tom , Riahi, Ardeshir
IPC分类号： F01D5/08 , F01D5/04 , F04D29/28
CPC分类号： F01D5/026 , F01D1/24 , F01D5/04 , F01D5/066 , F01D5/085 , F01D5/088 , F01D5/18 , F04D29/28 , F05D2230/23 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： An axially-split radial turbine (20) includes a forward rotor section (50) and an aft rotor section (52) being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis (26) of the axially-split radial turbine. The axially-split radial turbine (20) can be provided as part of a gas turbine engine (18).
摘要翻译：轴向分开的径流式涡轮机（20）包括沿着环形界面彼此机械地且邻接地联接的前部转子部分（50）和后部转子部分（52），所述环形界面位于大致垂直于旋转轴线（26 ）的轴向分开的径流式涡轮机。轴向分开的径流式涡轮机（20）可以设置为燃气涡轮发动机（18）的一部分。

7. 发明公开

EP2937518A1 GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF 有权转让
标题翻译：带密封张力释放槽及其制造方法的燃气涡轮发动机部件
公开(公告)号：EP2937518A1
公开(公告)日：2015-10-28
申请号：EP15154580.3
申请日：2015-02-10
申请人： Honeywell International Inc.
发明人： Smoke, Jason , Tucker, Bradley Reed , Riahi, Ardeshir , Zurmehly, Ed , Mirzamoghadam, Alexander
IPC分类号： F01D9/04 , F01D11/00
CPC分类号： F01D11/005 , B22D19/00 , B22D25/02 , B22D25/06 , F01D1/06 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/30 , F05D2240/55 , F05D2260/20 , F05D2260/941
摘要： Embodiments of a gas turbine engine component (60) having sealed stress relief slots are provided, as are embodiments of a gas turbine engine (20) containing such a component. In one embodiment, the gas turbine engine includes a core gas flow path (92), a secondary cooling flow path (94), and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body (62, 64, 66) through which the core gas flow path extends, a radially-extending wall (70) projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots (74) formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material (104), which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during gas turbine engine operation.
摘要翻译：具有密封的燃气涡轮发动机组件（60）的实施例，提供应力消除狭槽，作为是含有搜索组件的燃气涡轮发动机（20）的实施例。在一个中，实施例的燃气涡轮发动机包括核心燃气流动路径（92），二次冷却流路（94），和一个涡轮喷嘴或其它燃气涡轮发动机构件。所述部件包括，反过来，一个组件体（62，64,66），通过该芯气体流动路径延伸，一个径向延伸的壁（70）从组件主体并进入二次冷却流路投影，以及一个或在径向延伸的壁形成更多的应力释放槽（74）。应力消除狭槽填充有第二冷却之间妨碍泄漏和coregas流动路径和骨折燃气涡轮发动机操作期间，径向延伸的壁内，以减轻热机械应力的高温密封材料（104）。

8. 发明公开

EP2851511A3 Turbine blades with tip portions having converging cooling holes 有权转让
标题翻译：涡轮机叶片具有与会聚Schaufelspitzenbschnitten冷却孔
公开(公告)号：EP2851511A3
公开(公告)日：2015-05-06
申请号：EP14182739.4
申请日：2014-08-28
申请人： Honeywell International Inc.
发明人： Bedrosyan, Loris , Riahi, Ardeshir , Crites, Daniel C.
IPC分类号： F01D5/18 , F01D5/20 , F01D11/10
CPC分类号： F01D5/20 , F01D5/186 , F01D5/187 , F01D11/10 , F05D2240/307 , F05D2260/20 , Y02T50/673 , Y02T50/676
摘要： A turbine rotor blade (260) is provided for a turbine section of an engine that includes a shroud (210) surrounding the rotor blade. The rotor blade includes a platform (350) and an airfoil (310) extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap (330) extending between the suction side wall and the pressure side wall, a first squealer tip extension (332) extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole (400) that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.

9. 发明公开

EP2787174A2 Gas turbine engines with turbine airfoil cooling 有权转让
标题翻译： Gauferinentriebwerke mitgekühlteSchaufeln
公开(公告)号：EP2787174A2
公开(公告)日：2014-10-08
申请号：EP14161162.4
申请日：2014-03-21
申请人： Honeywell International Inc.
发明人： Crites Daniel Cregg , Morris, Mark C. , Crosatti, Lorenzo , Riahi, Ardeshir
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： An airfoil (310) for a gas turbine engine is provided. The airfoil includes a body (311) with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall (402) disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber (424) and a leading edge chamber (422). The interior wall defines a cooling hole (450) with a base portion (470) and a locally extended portion (480) to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
摘要翻译：提供了一种用于燃气涡轮发动机的翼型件（310）。翼型件包括具有前缘的主体（311），后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。身体定义一个内腔。所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸以限定供应室（424）和前缘室（422）的内壁（402）。内壁限定具有基部（470）和局部延伸部分（480）的冷却孔（450），以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。

10. 发明公开

EP2653652A2 Axially-split radial turbine 有权转让
标题翻译：轴向自动涡轮机
公开(公告)号：EP2653652A2
公开(公告)日：2013-10-23
申请号：EP13162820.8
申请日：2013-04-08
申请人： Honeywell International Inc.
发明人： Jan, David K. , Zollars, Christopher , Rana, Rajiv , Polakis, Tom , Riahi, Ardeshir
IPC分类号： F01D5/02 , F01D5/08 , F01D5/18 , F01D5/04
CPC分类号： F01D5/026 , F01D1/24 , F01D5/04 , F01D5/066 , F01D5/085 , F01D5/088 , F01D5/18 , F04D29/28 , F05D2230/23 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： An axially-split radial turbine (20) includes a forward rotor section (50) and an aft rotor section (52) being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis (26) of the axially-split radial turbine. The axially-split radial turbine (20) can be provided as part of a gas turbine engine (18).
摘要翻译：轴向分离的径向涡轮机（20）包括正向转子部分（50）和后转子部分（52），所述前转子部分（50）和后转子部分（52）沿着环形界面机械地和邻接地彼此耦合，所述环形界面位于大致垂直于旋转轴线）轴向分离的径向涡轮机。轴向分离的径向涡轮（20）可以被设置为燃气涡轮发动机（18）的一部分。

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