公开(公告)号：US20200024957A1

公开(公告)日：2020-01-23

申请号：US16239689

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Steven Bruce Gautschi

IPC: F01D5/14 ,  B22C9/10 ,  F01D5/18 ,  F01D5/28

Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.

公开(公告)号：US10436113B2

公开(公告)日：2019-10-08

申请号：US14816125

申请日：2015-08-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Dominic J. Mongillo ,  Steven Bruce Gautschi ,  Jaime G. Ghigliotty

IPC: F01D9/06 ,  F02C7/18 ,  F01D5/08 ,  F01D5/18 ,  F01D5/14 ,  F01D5/30 ,  F02C3/04 ,  F02C9/16

Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

公开(公告)号：US20190186291A1

公开(公告)日：2019-06-20

申请号：US15845727

申请日：2017-12-18

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Steven Bruce Gautschi

IPC: F01D25/12 ,  F02C7/18 ,  F01D9/04

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A skin core cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The skin core cooling passage is divided by a wall into two discrete first and second skin core cooling passages each supplied with cooling fluid from opposing sides.

公开(公告)号：US10012089B2

公开(公告)日：2018-07-03

申请号：US14704022

申请日：2015-05-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Steven Bruce Gautschi

IPC: F01D5/20 ,  F01D5/18 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/186 ,  F01D5/20 ,  F05D2220/32 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.

公开(公告)号：US09810084B1

公开(公告)日：2017-11-07

申请号：US14615509

申请日：2015-02-06

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Ryan Alan Waite ,  Steven Bruce Gautschi ,  Benjamin F. Hagan

IPC: F01D9/06 ,  F01D25/14 ,  F01D25/12

CPC classification number: F01D9/065 ,  F01D5/186 ,  F01D5/187 ,  F01D25/12 ,  F01D25/14 ,  F05D2240/126 ,  F05D2260/20 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/672 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.

公开(公告)号：US20170002663A1

公开(公告)日：2017-01-05

申请号：US14790231

申请日：2015-07-02

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott D. Lewis ,  Steven Bruce Gautschi ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

IPC: F01D5/18

CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.

Abstract translation: 燃气涡轮发动机翼型件包括提供沿径向方向延伸到尖端的外部翼面表面的主体。 外表面具有向前方向的前缘和向后方的后缘。 尖端包括具有凹陷表面的尖叫口袋。 冷却通道设置在体内。 每个冷却孔从冷却通道的入口延伸到凹陷表面处的出口。 入口和出口相对于凹入表面以角度方向成一定角度布置。 角度方向朝着前后方向中的至少一个方向。

公开(公告)号：US20160251968A1

公开(公告)日：2016-09-01

申请号：US14632485

申请日：2015-02-26

Applicant: United Technologies Corporation

Inventor： San Quach ,  Ryan Alan Waite ,  Christopher King ,  Steven Bruce Gautschi

IPC: F01D5/18 ,  F23R3/00 ,  F01D11/08 ,  F01D25/30 ,  F01D5/14 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D9/041 ,  F01D11/08 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/127 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/2214 ,  F23R3/002 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.

Abstract translation: 用于燃气涡轮发动机的翼型件包括翼型件，其包括在前缘和后缘处连接的间隔开的压力和抽吸侧壁，以提供从平台向尖端沿径向延伸的外部翼型件表面。 在后缘附近的压力侧和吸力侧壁之间设置空腔。 空腔包括由相对于彼此成角度布置的第一和第二出射区域界定的内部区域。 第一出口区域和第二出口区域分别相对于彼此在低压区域和高压区域中。 分别在第一和第二出口区域设置第一和第二基座组。 第二基座组具有各自终止的第一和第二基座。 第二基座的端部延伸超过第一基座的端部。

公开(公告)号：US09429027B2

公开(公告)日：2016-08-30

申请号：US14748666

申请日：2015-06-24

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo, Jr. ,  Steven Bruce Gautschi ,  San Quach

IPC: F01D5/08 ,  F01D5/20

CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.

Abstract translation: 翼型件包括压力表面和从翼型件的根部部分延伸到翼型件的尖端部分的抽吸表面。 翼型件还包括前缘和后缘，其在它们之间限定翼型的翼弦长度。 所述翼型件还包括沿所述翼型件的所述尖端部分在所述压力表面和尖端搁板壁之间形成的尖端架。 尖端架壁在压力表面和吸力表面之间间隔开，并且尖端架从从前缘测量的弦长的10％范围内延伸到从后缘测量的弦长的10％以内。

公开(公告)号：US20160084164A1

公开(公告)日：2016-03-24

申请号：US14816125

申请日：2015-08-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Dominic J. Mongillo ,  Steven Bruce Gautschi ,  Jaime G. Ghigliotty

IPC: F02C7/18 ,  F02C9/16 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/081 ,  F01D5/145 ,  F01D5/18 ,  F01D5/181 ,  F01D5/182 ,  F01D5/183 ,  F01D5/184 ,  F01D5/185 ,  F01D5/186 ,  F01D5/187 ,  F01D5/188 ,  F01D5/189 ,  F01D5/30 ,  F01D9/06 ,  F01D9/065 ,  F02C3/04 ,  F02C9/16 ,  F05D2220/32 ,  F05D2250/51 ,  F05D2250/71 ,  F05D2250/72 ,  F05D2250/73 ,  F05D2260/232 ,  Y02T50/676

Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

Abstract translation: 用于燃气涡轮发动机部件的冷却装置包括具有限定冷却流路的上游通道和下游通道的燃气涡轮发动机部件。 仪表特征包括至少一个孔，用于测量从上游通道到下游通道的流量，并具有上游侧和下游侧。 出口扩散器从仪表特征的下游侧向外延伸以控制在所需方向上的流向下游通道。 还公开了一种燃气涡轮发动机。

公开(公告)号：US20140075947A1

公开(公告)日：2014-03-20

申请号：US13621968

申请日：2012-09-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven Bruce Gautschi ,  Lane Thornton

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/00

CPC classification number: F01D5/189 ,  F05D2240/126 ,  Y02T50/676

Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling circuit disposed inside of the body portion. The cooling circuit includes a first baffle received within a first core cavity that extends inside of the body portion, a second baffle received within a second core cavity that extends inside of the body portion, and a first rib disposed between the first core cavity and the second core cavity. The first baffle is in fluid communication with the second baffle through the first rib.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括设置在主体部分内部的主体部分和冷却回路。 冷却回路包括容纳在主体部分内部延伸的第一芯腔内的第一挡板，容纳在主体部分内延伸的第二芯腔内的第二挡板，以及设置在第一芯腔和第二芯腔之间的第一肋 第二核心腔。 第一挡板通过第一肋与第二挡板流体连通。