公开(公告)号：US10711616B2

公开(公告)日：2020-07-14

申请号：US15353885

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Raymond Surace

IPC: F01D5/14 ,  F01D25/12 ,  F01D25/00 ,  F01D9/04 ,  F02C7/12 ,  F01D5/28 ,  F01D5/18 ,  F04D29/54

Abstract: An airfoil includes a core structure that has an airfoil portion that defines at least a portion of an airfoil profile. The airfoil portion has first and second opposed ends. A support wall extends from the first end. An endwall panel is attached to the support wall adjacent the airfoil portion.

公开(公告)号：US10577964B2

公开(公告)日：2020-03-03

申请号：US15475656

申请日：2017-03-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Raymond Surace ,  Renee J. Jurek ,  Tracy A. Propheter-Hinckley

IPC: F01D11/24 ,  F01D11/20 ,  F02C3/04 ,  F01D5/02 ,  F02C9/18 ,  F04D29/54 ,  F01D9/06

Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.

公开(公告)号：US10480331B2

公开(公告)日：2019-11-19

申请号：US15354260

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Eric A. Hudson ,  Raymond Surace

IPC: F01D5/28 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D25/00 ,  F04D29/02 ,  F04D29/38 ,  F04D29/54 ,  F02C3/04 ,  F01D5/14

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a distinct panel that forms a portion of the airfoil profile. The panel has a geometrically segmented coating section. The geometrically segmented coating section includes a wall that has an outer side. The outer side includes an array of cells, and there is a coating disposed in the array of cells.

公开(公告)号：US10415407B2

公开(公告)日：2019-09-17

申请号：US15354161

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Raymond Surace ,  Tracy A. Propheter-Hinckley

IPC: F01D5/14 ,  F01D9/04 ,  F02C3/04 ,  F01D25/00 ,  F04D29/38 ,  F01D5/18 ,  F01D5/28 ,  F01D25/12

Abstract: An airfoil includes an airfoil section that defines an airfoil profile, and a first endwall section with which the airfoil section is attached. First and second airfoil pieces form different portions of the airfoil profile. The first and second airfoil pieces include respective first ends. The first ends interlock with the first endwall section such that the first and second airfoil pieces are retained with the first endwall section.

公开(公告)号：US10309226B2

公开(公告)日：2019-06-04

申请号：US15353874

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Raymond Surace

IPC: F01D5/28 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12 ,  F01D5/18 ,  F02C7/12

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a panel that forms a portion of the airfoil profile and a core structure to which the panel is secured.

公开(公告)号：US20180298774A1

公开(公告)日：2018-10-18

申请号：US15490304

申请日：2017-04-18

Applicant: United Technologies Corporation

Inventor： Daniel Carlson ,  Jonathan Ortiz ,  Matthew A. Devore ,  Raymond Surace

IPC: F01D11/04 ,  F01D5/06 ,  F01D9/04 ,  F01D11/00

CPC classification number: F01D11/04 ,  F01D5/06 ,  F01D5/082 ,  F01D9/041 ,  F01D11/001 ,  F01D11/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/56 ,  F05D2260/14 ,  F05D2260/601

Abstract: Gas turbine engines and turbines thereof including a stator section having a plurality of vanes, a rotating section having a plurality of blades, the rotating section being axially adjacent the stator section along an axis of the turbine, the stator section being aftward of the rotating section along the axis of the turbine, and a primary tangential onboard injector located radially inward from the stator section and configured to direct an airflow from the stator section in a forward direction toward the rotating section, the primary tangential onboard injector turning the airflow in a direction of rotation of the rotating section.

公开(公告)号：US20180135427A1

公开(公告)日：2018-05-17

申请号：US15353840

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Raymond Surace

IPC: F01D5/18 ,  F01D9/04 ,  F01D5/28 ,  F01D25/08 ,  F02C3/04 ,  F04D29/54 ,  F04D29/32 ,  F04D29/58

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/284 ,  F01D9/041 ,  F01D25/08 ,  F02C3/04 ,  F04D29/324 ,  F04D29/541 ,  F04D29/582 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/202 ,  F05D2300/20 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a core structure and a hollow panel adjacent to the core structure. The hollow panel forms at least a portion of a leading end of the airfoil profile.

公开(公告)号：US20180135422A1

公开(公告)日：2018-05-17

申请号：US15354097

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Raymond Surace

IPC: F01D5/14 ,  F01D9/04 ,  F04D29/54 ,  F04D29/38 ,  F01D5/18 ,  F01D5/28 ,  F04D29/02 ,  F04D29/58 ,  F02C3/04

Abstract: An airfoil includes an airfoil section defining an airfoil profile, the airfoil section including a core structure and a plurality of rods disposed adjacent the core structure.

公开(公告)号：US20160298484A1

公开(公告)日：2016-10-13

申请号：US15036856

申请日：2014-11-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John D. Teixeira ,  Thomas N. Slavens ,  Raymond Surace

IPC: F01D17/16 ,  F01D25/12 ,  F04D29/056 ,  F01D9/04 ,  F04D29/56 ,  F04D29/58

CPC classification number: F01D17/162 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F01D11/005 ,  F01D25/12 ,  F04D29/056 ,  F04D29/563 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2260/20

Abstract: A gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening.

Abstract translation: 具有可调节叶片的燃气涡轮发动机包括具有孔和孔的平台。 一个叶片被支承在相对于平台的旋转中，通过一个容纳在孔中的木耳。 叶片具有与杆状体横向间隔开并与孔对准的开口。 叶片包括具有与开口流体连通的冷却通道的翼型件。

公开(公告)号：US20150361822A1

公开(公告)日：2015-12-17

申请号：US14762302

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey ,  Raymond Surace ,  Tracy A. Propheter-Hinckley

IPC: F01D17/16

CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D5/187

Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.

Abstract translation: 用于涡轮发动机的可调节定子叶片包括轴，凸缘和绕可变叶片轴线枢转的定子叶片体。 定子叶片体在第一端和第二端之间轴向延伸。 定子叶片主体包括翼型件，空腔和位于第一端的主体表面。 空腔从体表面的入口轴向延伸到翼型中。 轴从第一端沿着可变叶片轴线延伸。 凸缘围绕入口和轴周向延伸，并且从定子叶片体径向延伸。