公开(公告)号：US20170089206A1

公开(公告)日：2017-03-30

申请号：US14871456

申请日：2015-09-30

Applicant: United Technologies Corporation

Inventor： San Quach ,  Steven Bruce Gautschi ,  Matthew A. Devore ,  Scott D. Lewis ,  Matthew S. Gleiner ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D5/20 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.

公开(公告)号：US20170051623A1

公开(公告)日：2017-02-23

申请号：US14830812

申请日：2015-08-20

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Dominic J. Mongillo, JR. ,  Matthew A. Devore

IPC: F01D11/08 ,  F01D25/12

CPC classification number: F01D11/08 ,  F01D25/12 ,  F05D2240/11 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2260/2212 ,  Y02T50/676

Abstract: A gas turbine engine component includes a wall portion and a leading edge cooling channel that extends through the wall portion. The leading edge cooling channel includes at least one first cooling passage separated from at least one serpentine cooling passage.

Abstract translation: 燃气涡轮发动机部件包括延伸穿过壁部的壁部和前缘冷却通道。 前缘冷却通道包括与至少一个蛇形冷却通道分离的至少一个第一冷却通道。

公开(公告)号：US20160208619A1

公开(公告)日：2016-07-21

申请号：US14602035

申请日：2015-01-21

Applicant: United Technologies Corporation

Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

Abstract translation: 提供翼型。 所述翼型件可以包括十字交叉，与所述十字架流体连通的冲击室以及设置在所述冲击室的第一表面上的第一跳闸条。 还提供冷却系统。 冷却系统可以包括冲击室，冲击室的第一表面上的第一跳闸条和在冲击室的第二表面上的第二跳闸条。 还提供内部冷却的发动机部件。 内部冷却部分可以包括与交叉流体连通的交叉和冲击室。 十字架可以构造成将空气引向冲击室的第一表面。 第一跳闸条可以设置在冲击室的第一表面上。

公开(公告)号：US20160108738A1

公开(公告)日：2016-04-21

申请号：US14854213

申请日：2015-09-15

Applicant: United Technologies Corporation

Inventor： Matthew A. Devore ,  Matthew S. Gleiner

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/18 ,  F01D9/023 ,  F01D25/12 ,  F05D2240/81 ,  F05D2260/20 ,  F05D2260/201 ,  Y02T50/676

Abstract: A gas turbine engine component includes an airfoil that extends from a first side of a platform and a cooling passage that extends through the platform and includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the airfoil.

Abstract translation: 燃气涡轮发动机部件包括从平台的第一侧延伸的翼型件和延伸穿过所述平台并且包括位于所述平台的第二相对侧上的入口的冷却通道。 入口位于翼型的轴向上游。

公开(公告)号：US20160032416A1

公开(公告)日：2016-02-04

申请号：US14883060

申请日：2015-10-14

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Dominic J. Mongillo, Jr. ,  Matthew A. Devore ,  Steven Bruce Gautschi ,  Benjamin T. Fisk

IPC: C21D9/00 ,  B22F3/10 ,  B22F3/105 ,  B23K15/00 ,  B22F5/04

CPC classification number: B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  B22F3/1017 ,  B22F3/105 ,  B22F3/1055 ,  B22F5/04 ,  B23K15/0086 ,  B33Y10/00 ,  B33Y80/00 ,  C21D9/0068 ,  F01D5/187 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  Y02P10/292 ,  Y02P10/295

Abstract: A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to CAD data relating to a particular cross-section of an airfoil. The airfoil is produced with leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. An exterior wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the exterior wall to provide an impingement cavity between the exterior wall and the impingement wall. Multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall.

Abstract translation: 一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积在彼此上。 参考与翼型的特定横截面相关的CAD数据，这些层彼此连接。 翼型件被制造成具有通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 外墙在前缘提供外部翼型表面。 冲击壁与外壁一体地形成，以在外壁和冲击壁之间提供冲击腔。 多个冲击孔设置在冲击壁上。 冲击孔横向穿过冲击壁间隔开。

公开(公告)号：US20140199177A1

公开(公告)日：2014-07-17

申请号：US13737200

申请日：2013-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  San Quach ,  Matthew A. Devore

IPC: F01D5/18 ,  B23P15/04

CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  F01D5/186 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  Y10T29/49337

Abstract: An airfoil includes leading and trailing edges, a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces, a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces, and cavities within the airfoil. A first cavity extends along the inner surface of the first exterior wall and a first inner wall and has an upstream end and a downstream end, and a feed cavity is located between the first inner wall and the second exterior wall.

Abstract translation: 机翼包括前缘和后缘，从前缘延伸到后缘并具有内表面和外表面的第一外壁，从前缘延伸到后缘的第二外壁，大体与第一外壁相对，并且具有内 和外表面以及翼型内的空腔。 第一腔沿着第一外壁的内表面延伸并且具有第一内壁并具有上游端和下游端，并且进料腔位于第一内壁和第二外壁之间。

公开(公告)号：US10947854B2

公开(公告)日：2021-03-16

申请号：US16793575

申请日：2020-02-18

Applicant: United Technologies Corporation

Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

公开(公告)号：US10808554B2

公开(公告)日：2020-10-20

申请号：US15354055

申请日：2016-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Michael G. McCaffrey ,  Raymond Surace ,  Matthew A. Devore

IPC: F01D5/28 ,  F01D9/06 ,  B32B18/00 ,  F01D9/04 ,  B23P15/04 ,  F01D5/18 ,  F01D25/12 ,  F04D29/38 ,  F04D29/54 ,  F01D5/14

Abstract: A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.

公开(公告)号：US10738619B2

公开(公告)日：2020-08-11

申请号：US15107493

申请日：2015-01-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lane Thornton ,  Matthew A. Devore ,  Dominic J. Mongillo ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.

公开(公告)号：US10711624B2

公开(公告)日：2020-07-14

申请号：US15353896

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Matthew A. Devore ,  Adam P. Generale ,  Tracy A. Propheter-Hinckley

IPC: F01D5/28 ,  F01D9/04 ,  F01D25/08 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F02C3/04 ,  F01D5/14

Abstract: An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells.