公开(公告)号：US11118471B2

公开(公告)日：2021-09-14

申请号：US15027526

申请日：2014-10-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John D. Teixeira ,  Eric A. Grover ,  Raymond Surace

IPC: F01D17/16 ,  F01D5/14

Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.

公开(公告)号：US20210095596A1

公开(公告)日：2021-04-01

申请号：US16587684

申请日：2019-09-30

Applicant: United Technologies Corporation

Inventor： Renee Behlman ,  Tracy Propheter-Hinckley ,  Raymond Surace ,  Matthew Devore

IPC: F02C7/12 ,  F01D25/12

Abstract: A flowpath component for a gas turbine engine includes a body having a leading edge and a trailing edge. A first exterior wall connects the leading edge to the trailing edge and a second exterior wall connects the leading edge to the trailing edge. At least one first internal cooling passage has a first inlet at a first end of the body. At least one second internal cooling passage has a second inlet at a second end of the body. The at least one first internal cooling passage is isolated from the at least one second internal cooling passage.

公开(公告)号：US10808554B2

公开(公告)日：2020-10-20

申请号：US15354055

申请日：2016-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/28 ,  F01D9/06 ,  B32B18/00 ,  F01D9/04 ,  B23P15/04 ,  F01D5/18 ,  F01D25/12 ,  F04D29/38 ,  F04D29/54 ,  F01D5/14

Abstract: A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.

公开(公告)号：US10598025B2

公开(公告)日：2020-03-24

申请号：US15354097

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Raymond Surace

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

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：US10385720B2

公开(公告)日：2019-08-20

申请号：US15036856

申请日：2014-11-03

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D9/04 ,  F01D9/06 ,  F01D11/00 ,  F01D17/16 ,  F01D25/12 ,  F04D29/56 ,  F04D29/58 ,  F04D29/056

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.

公开(公告)号：US10240479B2

公开(公告)日：2019-03-26

申请号：US14909209

申请日：2014-08-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Raymond Surace

IPC: F01D9/04 ,  F01D9/06 ,  F02C9/20 ,  F01D17/16

Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at least a first variable vane row and a second turbine section downstream from the first turbine section and having at least a second variable vane row. A transition duct is disposed between the first turbine section and the second turbine section.

公开(公告)号：US20180135445A1

公开(公告)日：2018-05-17

申请号：US15354161

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Raymond Surace ,  Tracy A. Propheter-Hinckley

IPC: F01D9/04 ,  F02C3/04 ,  F01D25/00

CPC classification number: F01D9/042 ,  F01D5/141 ,  F01D5/147 ,  F01D5/187 ,  F01D5/282 ,  F01D9/041 ,  F01D25/005 ,  F01D25/12 ,  F02C3/04 ,  F04D29/388 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/30 ,  F05D2300/20 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

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：US11459899B2

公开(公告)日：2022-10-04

申请号：US15934332

申请日：2018-03-23

Applicant: United Technologies Corporation

Inventor： Dilip M. Shah ,  Alan D. Cetel ,  Venkatarama K. Seetharaman ,  Raymond Surace

IPC: F01D5/18

Abstract: A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

公开(公告)号：US11300209B2

公开(公告)日：2022-04-12

申请号：US16598168

申请日：2019-10-10

Applicant: United Technologies Corporation

Inventor： Jeremy Drake ,  Raymond Surace

IPC: F16J15/3288 ,  F01D11/00 ,  F01D11/12 ,  F04D29/08

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

公开(公告)号：US11118474B2

公开(公告)日：2021-09-14

申请号：US15727816

申请日：2017-10-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Raymond Surace

IPC: F01D25/12 ,  F01D9/04 ,  F23R3/00 ,  F02C7/18 ,  F01D5/18 ,  F01D5/14

Abstract: A vane platform cooling system may comprise a combustor shell and a combustor panel. A cavity may be located between the combustor shell and the combustor panel. A surface of the cavity may be angled toward the combustor shell. An orifice may be formed in a vane platform located aft of the combustor panel. A standoff located in the cavity may direct air toward the vane platform. An aperture may be formed in a surface of the vane platform. A channel formed through the vane platform may connect the orifice and aperture.