公开(公告)号：US10352172B2

公开(公告)日：2019-07-16

申请号：US14914304

申请日：2014-09-02

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/14 ,  F01D5/18 ,  F01D9/04 ,  F01D11/08

Abstract: A dual wall component includes a first outer wall extending from a leading edge to a trailing edge, a first inner wall spaced from the first outer wall by a plurality of first cavities and first ribs, a second inner wall spaced from the first inner wall by a plurality of second cavities and second ribs, and a second outer wall extending from the leading edge to the trailing edge and spaced from the second inner wall by a plurality of third cavities and third ribs. Portions of the first and second outer walls have thicknesses less than about 0.018″ (0.457 mm). In a method for forming a dual wall component, component walls are formed by additive manufacturing and without using cores to form the cavities.

公开(公告)号：US10329933B2

公开(公告)日：2019-06-25

申请号：US14660585

申请日：2015-03-17

Applicant: United Technologies Corporation

Inventor： Richard N. Allen ,  Brandon W. Spangler

IPC: F01D9/06 ,  F01D5/18

Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.

公开(公告)号：US20190186277A1

公开(公告)日：2019-06-20

申请号：US16283279

申请日：2019-02-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F01D11/20

CPC classification number: F01D9/023 ,  F01D5/186 ,  F01D5/288 ,  F01D9/065 ,  F01D11/20 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/12 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.

公开(公告)号：US20190170014A1

公开(公告)日：2019-06-06

申请号：US15832925

申请日：2017-12-06

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Adam P. Generale ,  Ky H. Vu

IPC: F01D25/12 ,  F01D9/04

Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.

公开(公告)号：US20190170002A1

公开(公告)日：2019-06-06

申请号：US15832948

申请日：2017-12-06

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Adam P. Generale ,  Ky H. Vu

IPC: F01D9/02 ,  F01D9/04 ,  F02C3/04 ,  F02C7/141

Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.

公开(公告)号：US10280841B2

公开(公告)日：2019-05-07

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

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.

公开(公告)号：US10273808B2

公开(公告)日：2019-04-30

申请号：US14938310

申请日：2015-11-11

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo ,  Edward F. Pietraszkiewicz

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

Abstract: An airfoil of a gas turbine engine is provided. The airfoil includes an airfoil body having at least one internal flow passage, the body having a first surface and a second surface, the first surface defining a wall of the at least one internal flow passage and a bleed port fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice extending from the second surface toward the internal flow passage and a bleed port cavity extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.

公开(公告)号：US20190078786A1

公开(公告)日：2019-03-14

申请号：US15699163

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Atul Kohli ,  Brandon W. Spangler ,  David J. Hyland ,  Dustin W. Davis ,  Ricardo Trindade ,  Stephen K. Kramer ,  Steven Bruce Gautschi

IPC: F23R3/60 ,  F23R3/00 ,  F16B37/00

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

公开(公告)号：US20190078785A1

公开(公告)日：2019-03-14

申请号：US15698967

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R3/06 ,  F23R3/54 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

公开(公告)号：US20180306036A1

公开(公告)日：2018-10-25

申请号：US15496093

申请日：2017-04-25

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo

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

Abstract: Turn caps for airfoils of gas turbine engines having exterior side walls, an exterior top wall extending between the exterior side walls, a first turn cap divider extending from the exterior top wall and positioned between the exterior side walls and defining a first turning feature between the first turn cap divider and the exterior side walls, the first turning feature comprising a first suction-side turn passage and a first pressure-side turn passage wherein the first turn cap divider fluidly separates the first pressure-side turn passage from the first suction-side turn passage within the turn cap, and a merging chamber is formed in the turn cap wherein fluid flows passing through the first suction side turn passage and the first pressure side turn passage are merged at the merging chamber.