公开(公告)号：WO2015026416A3

公开(公告)日：2015-04-16

申请号：PCT/US2014039710

申请日：2014-05-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KNOWLTON ROBERT ,  ASTERLIN MAX ,  RAPP BRANDON M ,  JARIWALA PARTH

IPC: F01D5/16 ,  F01D5/10

CPC classification number: F01D5/10 ,  F01D5/081 ,  F01D5/18 ,  F01D5/26 ,  F01D11/006 ,  F05D2240/57 ,  F05D2260/96 ,  Y02T50/676

Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.

Abstract translation: 描述了涡轮叶片减振器。 阻尼器具有轴向延伸的主体，其限定内表面和相对的阻尼表面。 主体还具有从内表面到阻尼表面的边缘，并且延伸穿过主体的开槽孔。 开槽孔在内表面和阻尼表面之间延伸。 相邻的开槽孔对形成了限定纵向轴线的细长形状，该轴线在阻尼器表面的一个点处相交。

公开(公告)号：WO2014186005A3

公开(公告)日：2015-02-26

申请号：PCT/US2014015194

申请日：2014-02-07

Applicant: UNITED TECHNOLOGIES CORP

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 ,  F01D9/023 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/02

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 包括气体通道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所述非气体通道表面延伸到 气路面。

公开(公告)号：EP2867501A4

公开(公告)日：2015-07-08

申请号：EP13810147

申请日：2013-05-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZELESKY MARK F ,  TRINDADE RICARDO ,  TELLER BRET M ,  LEWIS SCOTT D ,  BEATTIE JEFFREY S ,  JACQUES JEFFREY MICHAEL ,  RAPP BRANDON M

IPC: F02C7/12 ,  F01D5/08 ,  F01D5/18 ,  F02K3/00

CPC classification number: F01D5/085 ,  F01D5/081 ,  F01D5/18 ,  F05D2240/81 ,  Y02T50/676

Abstract: A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.

公开(公告)号：EP2956627A4

公开(公告)日：2016-09-28

申请号：EP14797049

申请日：2014-02-07

Applicant: UNITED TECHNOLOGIES CORP

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 ,  F01D11/24 ,  F01D25/12 ,  F02C7/18 ,  F04D29/58

CPC classification number: F01D5/186 ,  F01D9/023 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/02

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：EP3004557A4

公开(公告)日：2017-02-15

申请号：EP14837891

申请日：2014-05-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KNOWLTON ROBERT ,  ASTERLIN MAX ,  RAPP BRANDON M ,  JARIWALA PARTH

IPC: F01D5/08 ,  F01D5/26 ,  F01D11/00

CPC classification number: F01D5/10 ,  F01D5/081 ,  F01D5/18 ,  F01D5/26 ,  F01D11/006 ,  F05D2240/57 ,  F05D2260/96 ,  Y02T50/676

Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.

Abstract translation: 描述了涡轮叶片减振器。 阻尼器具有限定内表面和相对的阻尼表面的轴向延伸主体。 主体还具有从内表面延伸到阻尼表面的边缘和延伸穿过主体的开槽孔。 开槽孔在内表面和阻尼表面之间延伸。 相邻的一对槽孔具有细长的形状，其限定纵向轴线，所述纵向轴线在阻尼器的表面处的点处相交。

公开(公告)号：EP2971555A4

公开(公告)日：2017-02-01

申请号：EP14773520

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOUGH MATTHEW ANDREW ,  RAPP BRANDON M

IPC: F01D5/26 ,  F01D5/12 ,  F02C7/00

CPC classification number: F01D5/10 ,  F01D5/26 ,  F01D5/3007 ,  F01D11/006 ,  F05D2260/96 ,  Y10T29/49323

Abstract: A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.

公开(公告)号：EP2971556A4

公开(公告)日：2016-11-23

申请号：EP14779530

申请日：2014-03-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： RAPP BRANDON M ,  HOUGH MATTHEW ANDREW

IPC: F01D5/22 ,  F01D5/30 ,  F01D11/00

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.