公开(公告)号：US10280761B2

公开(公告)日：2019-05-07

申请号：US14872272

申请日：2015-10-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ky H. Vu ,  Brandon W. Spangler

IPC: F01D5/18 ,  F23R3/04

Abstract: A component for use in a gas turbine engine comprises a body and a micro-core cooling circuit embedded within the body. The micro-core circuit has a variation in either the thickness or contoured surface, away from a generally planar shape to a non-planar shape.

公开(公告)号：US20190091760A1

公开(公告)日：2019-03-28

申请号：US16200970

申请日：2018-11-27

Applicant: United Technologies Corporation

Inventor： Lea D. Castle ,  Brandon W. Spangler

IPC: B22C9/10 ,  B22C9/12 ,  B22D25/02 ,  F01D5/28 ,  F01D9/02 ,  B22C3/00 ,  B22C7/02 ,  B22C9/24 ,  B22D29/00 ,  B22D29/04

CPC classification number: B22C9/103 ,  B22C3/00 ,  B22C7/02 ,  B22C9/108 ,  B22C9/12 ,  B22C9/24 ,  B22D25/02 ,  B22D29/001 ,  B22D29/04 ,  F01D5/28 ,  F01D5/284 ,  F01D9/02 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2300/175

Abstract: A casting core assembly includes a metallic core, a ceramic core having a compartment in which the portion of the metallic core is received, and a ceramic coating at least partially covering the metallic core and the ceramic core.

公开(公告)号：US10227927B2

公开(公告)日：2019-03-12

申请号：US14900730

申请日：2014-07-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Ricardo Trindade

IPC: F01D9/06 ,  F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F01D25/08 ,  F01D25/14 ,  F02C3/04 ,  F02C6/08

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.

公开(公告)号：US20190071980A1

公开(公告)日：2019-03-07

申请号：US15696259

申请日：2017-09-06

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Atul Kohli

IPC: F01D5/18

Abstract: Airfoils and gas turbine engines having the same, the airfoils including an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity defined within the airfoil body, wherein at least one wall of the cooling cavity is a curved end wall, and an end wall contoured pedestal positioned adjacent the curved end wall. The end wall contoured pedestal has a first portion with a contoured side wall and a parallel side wall, and a second portion with tapering side walls, wherein the contoured side wall faces the curved end wall, the contoured side wall paralleling a contour of the curved end wall and defining a meter section therebetween.

公开(公告)号：US20180283687A1

公开(公告)日：2018-10-04

申请号：US15476431

申请日：2017-03-31

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Atul Kohli ,  Dustin W. Davis ,  Ricardo Trindade ,  Steven Bruce Gautschi ,  Brandon W. Spangler ,  Trevor Rudy ,  Benjamin Bellows ,  Dave J. Hyland ,  James B. Hoke ,  Stephen K. Kramer ,  Dennis M. Moura

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F16B43/00 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

公开(公告)号：US20180195397A1

公开(公告)日：2018-07-12

申请号：US15404252

申请日：2017-01-12

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

Abstract: Airfoils having hollow bodies defining first and second airfoil cavities and having inner and outer diameter ends, a first airfoil platform at one end of the hollow body having a gaspath surface and a non-gaspath surface, wherein the hollow body extends from the gaspath surface. A first cavity opening is formed in the non-gaspath surface of the platform to fluidly connect to the first airfoil cavity and a second cavity opening in the platform is fluidly connected to the second airfoil cavity. A first turn cap is fixedly attached to the first airfoil platform on the non-gaspath surface covering the first and second cavity openings of the first airfoil platform and defines a first turning cavity such that the first cavity opening in the first airfoil platform is fluidly connected to the second cavity opening in the first airfoil platform by the first turning cavity.

公开(公告)号：US10006295B2

公开(公告)日：2018-06-26

申请号：US14893795

申请日：2014-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo

IPC: F01D5/18 ,  F01D5/02 ,  F01D9/04 ,  F01D25/12

CPC classification number: F01D5/188 ,  F01D5/02 ,  F01D5/189 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.

公开(公告)号：US09803489B2

公开(公告)日：2017-10-31

申请号：US14752143

申请日：2015-06-26

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D9/04 ,  F01D5/18 ,  F01D5/02 ,  F01D25/12

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/187 ,  F01D5/188 ,  F01D5/189 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2240/126 ,  F05D2250/185 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A vane includes a forward rib and an aft rib positioned axially aft of the forward rib. The vane also includes a middle rib positioned axially between the forward rib and the aft rib, such that the forward rib and the middle rib define a forward passage configured to receive a forward baffle and the middle rib and the aft rib define an aft passage configured to receive an aft baffle. The vane also includes an inner surface extending axially from the forward rib to the aft rib, being radially separated from the middle rib via a gap such that air can flow between the aft passage and the forward passage via the gap, and having a radially outward curve from the forward rib to the middle rib and having a radially inward curve from the middle rib to the aft rib.

公开(公告)号：US20170198588A1

公开(公告)日：2017-07-13

申请号：US14993765

申请日：2016-01-12

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

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

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/81 ,  F05D2260/202

Abstract: A component for a gas turbine engine is provided. The component having: a platform secured to the component, the platform having an exterior surface in fluid communication with an internal cooling pocket of the platform via a plurality of cooling openings located in the platform; a channel in fluid communication with the internal cooling pocket; an internal cooling cavity in fluid communication with the channel via a feed opening extending through an internal wall of the component, wherein a portion of the channel and the feed opening are located below the internal cooling pocket; and a cover plate sealing the internal cooling pocket and the channel.

公开(公告)号：US20170159567A1

公开(公告)日：2017-06-08

申请号：US14961694

申请日：2015-12-07

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Atul Kohli

IPC: F02C7/18 ,  F01D25/08 ,  F01D5/18

CPC classification number: F02C7/18 ,  F01D5/18 ,  F01D5/188 ,  F01D25/08 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A method of increasing a heat transfer of a cooling fluid passing through a component of a gas turbine engine. The method including the steps of: directing a cooling fluid between an interior surface of an internal cooling cavity of the component and an exterior surface of a baffle insert located in the internal cooling cavity; and creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity, wherein the internal cooling cavity is elliptical in shape.