公开(公告)号：WO2014186005A2

公开(公告)日：2014-11-20

申请号：PCT/US2014/015194

申请日：2014-02-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： LEWIS, Scott D. ,  RAPP, Brandon M. ,  BEATTIE, Jeffrey S. ,  HOUGH, Matthew Andrew ,  TELLER, Bret M. ,  JACQUES, Jeffrey Michael ,  ASTERLIN, Max

CPC classification number: 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

Abstract: 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.

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尤其包括在前缘和后缘之间轴向延伸的平台，其周向地在第一配合面和第二配合面之间延伸，以及 包括气体路径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非气体通道表面延伸到 气路面。

公开(公告)号：WO2014164252A1

公开(公告)日：2014-10-09

申请号：PCT/US2014/021521

申请日：2014-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： RAPP, Brandon M. ,  HOUGH, Matthew Andrew

IPC: F01D5/26 ,  F01D5/12 ,  F02C7/00

CPC classification number: F01D5/26 ,  F01D5/02 ,  F01D5/12 ,  F01D5/22 ,  F01D5/3007 ,  F01D5/326 ,  F01D11/006 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/73 ,  F05D2260/96

Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.

Abstract translation: 用于燃气涡轮发动机转子组件的阻尼器密封件具有带前缘，后缘，压力侧和吸力侧的轴向细长主体。 细长体包括形成在前缘的压力侧的第一扩大部分和形成在与后缘相邻的吸入侧上的第二扩大部分。

公开(公告)号：WO2013180953A1

公开(公告)日：2013-12-05

申请号：PCT/US2013/041124

申请日：2013-05-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BEATTLE, Jeffrey S. ,  LEWIS, Scott D. ,  ZELESKY, Mark F. ,  TRINIDADE, Ricardo ,  TELLER, Bret M. ,  JACQUES, Jeffrey Michael ,  RAPP, Brandon M.

IPC: F02C7/12 ,  F01D5/18 ,  F01D25/12

CPC classification number: F01D5/085 ,  F01D5/081 ,  F01D5/187 ,  F01D25/12 ,  F05D2240/81

Abstract: A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.

Abstract translation: 燃气涡轮发动机部件包括护罩，U形通道，内部冷却空气通道和U形通道冷却孔。 护罩包括前表面，后表面，第一侧面和第二侧面。 U形通道设置在护罩的后面。 气路面连接前面，后面，第一侧面和第二侧面。 冷却表面将前面，后面，第一侧面和与气体通路面相对的第二侧面连接起来。 内部冷却空气通道延伸穿过护罩。 U通道冷却孔延伸到与U形槽相邻的护罩的第一侧面以与内部冷却通道相交。

公开(公告)号：EP2956627B1

公开(公告)日：2018-07-25

申请号：EP14797049.5

申请日：2014-02-07

Applicant: United Technologies Corporation

Inventor： LEWIS, Scott D. ,  RAPP, Brandon M. ,  BEATTIE, Jeffrey S. ,  HOUGH, Matthew Andrew ,  TELLER, Bret M. ,  JACQUES, Jeffrey Michael ,  ASTERLIN, Max

IPC: F01D5/18 ,  F01D5/08 ,  F01D25/12 ,  F02C7/18 ,  F04D29/58 ,  F01D11/24

CPC classification number: 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

Abstract: 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.

公开(公告)号：EP2956627A2

公开(公告)日：2015-12-23

申请号：EP14797049.5

申请日：2014-02-07

Applicant: United Technologies Corporation

Inventor： LEWIS, Scott D. ,  RAPP, Brandon M. ,  BEATTIE, Jeffrey S. ,  HOUGH, Matthew Andrew ,  TELLER, Bret M. ,  JACQUES, Jeffrey Michael ,  ASTERLIN, Max

IPC: F01D5/18 ,  F01D5/08 ,  F01D25/12 ,  F02C7/18 ,  F04D29/58

CPC classification number: 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

Abstract: 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.

公开(公告)号：EP2971556A1

公开(公告)日：2016-01-20

申请号：EP14779530.6

申请日：2014-03-07

Applicant: United Technologies Corporation

Inventor： RAPP, Brandon M. ,  HOUGH, Matthew Andrew

IPC: F01D5/26 ,  F01D5/12 ,  F02C7/00

CPC classification number: F01D5/26 ,  F01D5/02 ,  F01D5/12 ,  F01D5/22 ,  F01D5/3007 ,  F01D5/326 ,  F01D11/006 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/73 ,  F05D2260/96

Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.

Abstract translation: 用于燃气涡轮发动机转子组件的阻尼密封件具有带前缘，后缘，压力侧和吸力侧的轴向伸长的主体。 细长体包括在前缘处在压力侧上形成的第一扩大部分和在靠近后缘的吸力侧上形成的第二扩大部分。