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：EP2885520A4

公开(公告)日：2015-08-12

申请号：EP13829663

申请日：2013-08-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TELLER BRET M ,  ZELESKY MARK F ,  LEWIS SCOTT D ,  SPANGLER BRANDON W ,  TRINDADE RICARDO

IPC: F01D5/18 ,  F01D5/22 ,  F01D11/24

CPC classification number: F01D5/187 ,  F01D11/24 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/201 ,  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 and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.

公开(公告)号：EP3022421A4

公开(公告)日：2016-08-03

申请号：EP14826896

申请日：2014-07-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  TRINDADE RICARDO

IPC: F02C7/12 ,  F01D25/12 ,  F02C6/08

CPC classification number: F02C7/18 ,  F01D5/085 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/14 ,  F02C3/04 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/205 ,  F05D2260/232 ,  F05D2270/3062 ,  Y02T50/676

Abstract: In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser. A turbine section has at least one component to be cooled. A conduit is spaced from the diffuser and defines a cooling airflow path. The cooling airflow path is separate from an airflow downstream the diffuser, and passing to the combustor. The conduit passes cooling air to the component to be cooled.

Abstract translation: 在特征实施例中，燃气涡轮发动机具有压缩机部分，其具有下游转子和在压缩机部分下游的扩散器。 燃烧器在扩散器的下游接收空气。 涡轮部分具有至少一个待冷却的部件。 导管与扩散器间隔开并限定冷却气流路径。 冷却气流路径与扩散器下游的气流分离，并且通过燃烧器。 导管将冷却空气传递到要冷却的部件。

公开(公告)号：EP2880280A4

公开(公告)日：2016-07-13

申请号：EP13826145

申请日：2013-08-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AGGARWALA ANDREW S ,  ALLEN-BRADLEY EUNICE ,  GROVER ERIC A ,  TRINDADE RICARDO

IPC: F02C7/00 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/141 ,  F01D5/145 ,  F01D5/148 ,  F05D2240/124 ,  F05D2250/713

Abstract: An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.

Abstract translation: 用于燃气涡轮发动机的翼型件包括具有横截面的径向延伸的主体。 横截面包括前缘，后缘，压力侧和吸力侧。 压力侧以主要凹陷的曲率在前缘和后缘之间延伸。 吸入侧以主要凸起的曲率在前缘和后缘之间延伸。 吸入侧包括侧面为前后凸部的大致平坦部。 在另一个实施例中，吸入侧包括一系列局部曲率变化，其产生与后缘间隔开的吸入侧的凸曲率中的拐点。