公开(公告)号：US20160333699A1

公开(公告)日：2016-11-17

申请号：US15110904

申请日：2014-12-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James B. Downey, JR. ,  Brenda Zhang ,  Steven G. Lemieux ,  Eleanor D. Kaufman ,  Takao Fukuda ,  Daniel C. Nadeau

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02

CPC classification number: F01D5/18 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676 ,  Y02T50/6765

Abstract: An airfoil for a gas turbine engine includes pressure and suction surfaces that are provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extending to the trailing edge. The cooling passage terminates in a trailing edge exit that is arranged in the trailing edge. Multiple rows of pedestals include a first row of pedestals that join the pressure and suction walls. The first row of pedestals is arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.

Abstract translation: 用于燃气涡轮发动机的翼型件包括压力和抽吸表面，压力和吸力表面由沿径向延伸并在前缘和后缘连接的压力和吸力壁提供。 冷却通道设置在压力和吸力壁之间并延伸到后缘。 冷却通道终止于设置在后缘的后缘出口。 多排基座包括连接压力和吸力壁的第一排基座。 基座的第一排布置成最靠近后缘，但是位于后缘的内部，从而使后缘离开不受阻碍。

公开(公告)号：US10132168B2

公开(公告)日：2018-11-20

申请号：US15069738

申请日：2016-03-14

Applicant: United Technologies Corporation

Inventor： Jeffrey Leon ,  Daniel C. Nadeau ,  Jeffrey R. Levine ,  Eleanor D. Kaufman ,  Richard N. Allen ,  Evan P. Molony ,  Gregory Anselmi

IPC: F01D5/14 ,  F01D5/18 ,  F02C7/18 ,  B22C9/10

Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.

公开(公告)号：US20200291790A1

公开(公告)日：2020-09-17

申请号：US16415199

申请日：2019-05-17

Applicant: United Technologies Corporation

Inventor： Steven Taffet ,  Brandon S. Donnell ,  Daniel C. Nadeau ,  Russell Deibel ,  San Quach

IPC: F01D5/18 ,  B22C9/10 ,  B22C7/02 ,  B22C9/04 ,  B22C9/24 ,  F01D9/04 ,  F01D25/12

Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

公开(公告)号：US10370980B2

公开(公告)日：2019-08-06

申请号：US15039918

申请日：2014-11-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven Taffet ,  Brandon S. Donnell ,  Daniel C. Nadeau ,  Russell Deibel ,  San Quach

IPC: F01D5/18 ,  F01D25/12 ,  B22C9/04 ,  B22C7/02 ,  B22C9/24 ,  F01D9/04 ,  B22C9/10

Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

公开(公告)号：US10428666B2

公开(公告)日：2019-10-01

申请号：US15375827

申请日：2016-12-12

Applicant: United Technologies Corporation

Inventor： John David Forbes ,  Gregory Anselmi ,  Christina E. Botnick ,  Eleanor D. Kaufman ,  Jeffrey Leon ,  Jeffrey R. Levine ,  Gerald M. Mace ,  Daniel C. Nadeau ,  Tania Bhatia Kashyap ,  Richard N. Allen

IPC: F01D9/04 ,  F01D9/06

Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.

公开(公告)号：US20170260864A1

公开(公告)日：2017-09-14

申请号：US15069738

申请日：2016-03-14

Applicant: United Technologies Corporation

Inventor： Jeffrey Leon ,  Daniel C. Nadeau ,  Jeffrey R. Levine ,  Eleanor D. Kaufman ,  Richard N. Allen ,  Evan P. Molony ,  Gregory Anselmi

IPC: F01D5/18 ,  F02C7/18

CPC classification number: F01D5/187 ,  B22C9/10 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.

公开(公告)号：US20170022822A1

公开(公告)日：2017-01-26

申请号：US15039918

申请日：2014-11-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven Taffet ,  Brandon S. Donnell ,  Daniel C. Nadeau ,  Russell Deibel ,  San Quach

IPC: F01D5/18 ,  F01D25/12 ,  B22C9/04 ,  F01D9/04 ,  B22C7/02 ,  B22C9/24

CPC classification number: F01D5/187 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/323 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/202 ,  Y02T50/676

Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

Abstract translation: 失去的芯模组件包括第一腿部和第二腿部，其具有连接第一和第二腿部的多个交叉构件。 多个交叉构件包括彼此间隔开的最外侧交叉构件。 第一和第二腿部和第二交叉构件中的每一个的相邻端部比最外面的交叉构件彼此更靠近地间隔开。 中央交叉构件在第一和第二腿之间以及第二交叉构件之间延伸。 最外面的交叉构件延伸到第一横截面积。 第二交叉构件延伸到第二横截面积，并且中心交叉构件延伸第三横截面积。 第一截面积大于第二横截面积。 第二横截面积大于第三横截面积。 还公开了一种燃气涡轮发动机和部件。

公开(公告)号：US20180163551A1

公开(公告)日：2018-06-14

申请号：US15375827

申请日：2016-12-12

Applicant: United Technologies Corporation

Inventor： John David Forbes ,  Gregory Anselmi ,  Christina E. Botnick ,  Eleanor D. Kaufman ,  Jeffrey Leon ,  Jeffrey R. Levine ,  Gerald M. Mace ,  Daniel C. Nadeau ,  Tania Bhatia Kashyap ,  Richard N. Allen

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D9/065 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2250/74 ,  F05D2260/202

Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.