公开(公告)号：US11591914B2

公开(公告)日：2023-02-28

申请号：US16426036

申请日：2019-05-30

Applicant: United Technologies Corporation

Inventor： Dipanjan Saha ,  Brooks E. Snyder ,  Thomas N. Slavens

IPC: F01D5/18 ,  B23K26/34 ,  B33Y80/00 ,  B33Y10/00 ,  F01D9/04 ,  F01D25/12 ,  B22F5/04 ,  B22F7/08 ,  B23K101/00 ,  B22F10/20

Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.

公开(公告)号：US11168571B2

公开(公告)日：2021-11-09

申请号：US16745930

申请日：2020-01-17

Applicant: United Technologies Corporation

Inventor： David A. Niezelski ,  Timothy J. Jennings ,  Bret M. Teller ,  John McBrien ,  Thomas N. Slavens

IPC: F01D5/18 ,  F01D25/12

Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

公开(公告)号：US11143034B2

公开(公告)日：2021-10-12

申请号：US16408751

申请日：2019-05-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mark F. Zelesky

IPC: F01D5/14 ,  B22F5/04 ,  F01D5/18 ,  B22F7/08 ,  B23K1/00 ,  B23K15/00 ,  B23K26/34 ,  B23K31/02 ,  B22F10/20 ,  B23K26/342 ,  B21K3/04 ,  B22D21/00 ,  B22D25/02 ,  B22F3/24 ,  B23K10/02 ,  B23K26/00 ,  B23K101/00 ,  B23K103/04 ,  B23K103/08 ,  B23K103/14 ,  B23K103/16 ,  B33Y10/00 ,  B33Y80/00

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

公开(公告)号：US10960460B2

公开(公告)日：2021-03-30

申请号：US15112009

申请日：2015-01-23

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Thomas N. Slavens ,  Mark F. Zelesky ,  James T. Auxier

IPC: B22C9/04 ,  B33Y80/00 ,  B22C7/02 ,  B22C9/10 ,  B22F5/00 ,  B22F3/105 ,  B22F7/06 ,  B22C21/14 ,  B33Y10/00 ,  B22C1/00 ,  B29L31/00 ,  B29C64/153

Abstract: A mold for manufacturing a casted workpiece is, at least in-part, manufactured utilizing an additive manufacturing process. The mold may have a core having non-line-of-sight features that are additively manufactured and in contact with an outer shell of a wax mold and/or an outer shell of a casting mold of the mold. The outer shell of either the wax or casting molds may also be additively manufactured, and the shell of the casting mold may be additively manufactured as one unitary piece to the core.

公开(公告)号：US10519802B2

公开(公告)日：2019-12-31

申请号：US15497757

申请日：2017-04-26

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Edward F. Pietraszkiewicz ,  Thomas J. Martin ,  Mark F. Zelesky ,  Steven B. Gautschi ,  Matthew A. Devore ,  Alexander Staroselsky

IPC: F01D25/12 ,  F01D5/18 ,  F01D9/06 ,  F01D9/04 ,  F01D17/16

Abstract: A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.

公开(公告)号：US20190316474A1

公开(公告)日：2019-10-17

申请号：US16426036

申请日：2019-05-30

Applicant: United Technologies Corporation

Inventor： Dipanjan Saha ,  Brooks E. Snyder ,  Thomas N. Slavens

IPC: F01D5/18 ,  B33Y10/00 ,  B33Y80/00 ,  F01D9/04 ,  F01D25/12 ,  B23K26/34

Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.

公开(公告)号：US10385774B2

公开(公告)日：2019-08-20

申请号：US15268713

申请日：2016-09-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Tania Bhatia Kashyap ,  Mark F. Zelesky ,  Arthur W. Utay ,  Gabriel L. Suciu ,  Thomas N. Slavens ,  Kevin L. Rugg ,  Brian Merry

IPC: F02C3/107 ,  F02C3/14 ,  F02C7/04

Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

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：US10329921B2

公开(公告)日：2019-06-25

申请号：US14878498

申请日：2015-10-08

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Carey Clum

IPC: G01K1/14 ,  G01K13/02 ,  F01D5/18

Abstract: A component includes at least one thermal riser that extends from an exterior surface of the component. At least one cooling passage extends through a wall and adjoins an interior cooling passage and provides an exterior surface. At least one cooling passage is configured to direct cooling fluid through the wall adjacent to at least one thermocouple.

公开(公告)号：US10307817B2

公开(公告)日：2019-06-04

申请号：US14870443

申请日：2015-09-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mark F. Zelesky ,  JinQuan Xu ,  Joel H. Wagner

IPC: B22C9/10 ,  B22C9/24 ,  B22D29/00 ,  B22F3/105 ,  B29C67/00 ,  B22C1/00 ,  B22C9/02 ,  F01D5/18 ,  B22F5/00 ,  B22F5/04 ,  B33Y80/00 ,  B33Y10/00

Abstract: A casting article according to another exemplary aspect of the present disclosure includes, among other things, a circuit forming portion including an interior channel and an outer shell body that surrounds the interior channel. An engineered failure feature is formed in the outer shell body and is configured to increase compressibility of the casting article during a casting process.