公开(公告)号：US11268387B2

公开(公告)日：2022-03-08

申请号：US16239689

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr. ,  Steven Bruce Gautschi

IPC: F01D5/18 ,  F01D5/14 ,  B22C9/10 ,  F01D5/28

Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.

公开(公告)号：US10947854B2

公开(公告)日：2021-03-16

申请号：US16793575

申请日：2020-02-18

Applicant: United Technologies Corporation

Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

公开(公告)号：US10738619B2

公开(公告)日：2020-08-11

申请号：US15107493

申请日：2015-01-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lane Thornton ,  Matthew A. Devore ,  Dominic J. Mongillo ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.

公开(公告)号：US20200182070A1

公开(公告)日：2020-06-11

申请号：US16793575

申请日：2020-02-18

Applicant: United Technologies Corporation

Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

公开(公告)号：US20190203612A1

公开(公告)日：2019-07-04

申请号：US15856232

申请日：2017-12-28

Applicant: United Technologies Corporation

Inventor： Shawn M. McMahon ,  Christopher Whitfield ,  Nicholas M. LoRicco ,  Steven Bruce Gautschi ,  Vincent E. Simms ,  Justin M. Aniello ,  Thomas Allwood ,  Richard M. Salzillo ,  Jeffery Scott Hembree, SR.

IPC: F01D25/12 ,  F01D9/02

CPC classification number: F01D25/12 ,  F01D9/02 ,  F05D2220/32 ,  F05D2250/74 ,  F05D2260/202

Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

公开(公告)号：US20190078788A1

公开(公告)日：2019-03-14

申请号：US15699648

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A Propheter-Hinckley ,  Atul Kohli ,  Benjamin D Bellows ,  Dustin W Davis ,  James B Hoke ,  Stephen K Kramer ,  Steven Bruce Gautschi ,  Trevor Rudy

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03041

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：US20190078787A1

公开(公告)日：2019-03-14

申请号：US15699514

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Benjamin D Bellows ,  Brandon W Spangler ,  David J Hyland ,  Dennis M Moura ,  James B Hoke ,  Ricardo Trindade ,  Stephen K Kramer ,  Steven Bruce Gautschi

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R2900/03041

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：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：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：US10053992B2

公开(公告)日：2018-08-21

申请号：US14790231

申请日：2015-07-02

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott D. Lewis ,  Steven Bruce Gautschi ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

IPC: F01D5/18 ,  F01D5/20

CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.