公开(公告)号：US10815803B2

公开(公告)日：2020-10-27

申请号：US16521854

申请日：2019-07-25

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Dominic J. Mongillo, Jr. ,  Mark F. Zelesky ,  Bret M. Teller ,  Russell Deibel ,  Matthew S. Gleiner

IPC: F01D11/24 ,  F01D9/04 ,  F04D29/54 ,  F04D29/58 ,  F01D5/02 ,  F01D11/08 ,  F02C3/04 ,  F04D29/32

Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port. A method of cooling a component is also disclosed.

公开(公告)号：US10465523B2

公开(公告)日：2019-11-05

申请号：US14854213

申请日：2015-09-15

Applicant: United Technologies Corporation

Inventor： Matthew A. Devore ,  Matthew S. Gleiner

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

Abstract: A gas turbine engine component includes an airfoil that extends from a first side of a platform and a cooling passage that extends through the platform and includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the airfoil.

公开(公告)号：US10156144B2

公开(公告)日：2018-12-18

申请号：US14871456

申请日：2015-09-30

Applicant: United Technologies Corporation

Inventor： San Quach ,  Steven Bruce Gautschi ,  Matthew A. Devore ,  Scott D. Lewis ,  Matthew S. Gleiner ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

IPC: F01D5/18 ,  F01D5/20

Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.

公开(公告)号：US09482100B2

公开(公告)日：2016-11-01

申请号：US13629916

申请日：2012-09-28

Applicant: United Technologies Corporation

Inventor： Atul Kohli ,  Matthew S. Gleiner

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F23R3/06

CPC classification number: F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/73 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.

Abstract translation: 经受高温气体流动的燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括第一凸角，第二凸角和过渡区域。 第一个凸角从计量部分纵向和横向分开并具有第一形状。 第二叶片大致与第一叶片相对，并且从计量部分纵向和横向分叉并且具有不同于第一形状的第二形状。 过渡区域位于第一和第二凸角之间并且包括邻近出口的下游端。

公开(公告)号：US20160230577A1

公开(公告)日：2016-08-11

申请号：US15022725

申请日：2014-08-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Scott D. Lewis ,  Dominic J. Mongillo, JR. ,  Mark F. Zelesky ,  Bret M. Teller ,  Russell Deibel ,  Matthew S. Gleiner

IPC: F01D9/04 ,  F04D29/32 ,  F01D5/02 ,  F01D11/08 ,  F02C3/04

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D11/08 ,  F01D11/24 ,  F02C3/04 ,  F04D29/321 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2250/12 ,  F05D2260/201 ,  Y02T50/676

Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.

Abstract translation: 根据本公开的示例性方面的叶片包括从边缘面和间隔开的侧面之间延伸的平台以及从平台向外延伸的翼型件。 平台包括边缘面中的至少一个喷射口和连接到至少一个喷射口的至少一个通道。