公开(公告)号：US11014151B2

公开(公告)日：2021-05-25

申请号：US16705003

申请日：2019-12-05

Applicant: United Technologies Corporation

Inventor： John Joseph Marcin ,  Mark F. Zelesky ,  Joel H. Wagner ,  Theodore W. Hall ,  David A. Krause ,  Ben S. Reinert

IPC: B22C9/10 ,  B22C9/12 ,  B22C9/24 ,  B22C9/04 ,  B22D25/02 ,  B22D29/00 ,  B22C3/00 ,  B22C7/02 ,  B22F3/10 ,  B22F3/24 ,  B22F7/04 ,  B23K1/00 ,  B23K1/19 ,  B23K103/12 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58

Abstract: A method of making an airfoil includes making a refractory metal core that defines an interior of the airfoil by a tomo-lithographic process, making a mold that defines an exterior of the airfoil, inserting the refractory metal core into the mold, and pouring an airfoil material between the refractory metal core and the mold to cast the airfoil.

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：US10815803B2

公开(公告)日：2020-10-27

申请号：US16521854

申请日：2019-07-25

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Dominic J. Mongillo, Jr. ,  Mark F. Zelesky ,  Bret M. Teller ,  Russell Deibel ,  Matthew S. Gleiner

IPC: F01D11/24 ,  F01D9/04 ,  F04D29/54 ,  F04D29/58 ,  F01D5/02 ,  F01D11/08 ,  F02C3/04 ,  F04D29/32

Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port. A method of cooling a component is also disclosed.

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：US20190353046A1

公开(公告)日：2019-11-21

申请号：US15983904

申请日：2018-05-18

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Stephen K. Kramer

IPC: F01D11/08 ,  F23R3/00 ,  F01D9/04

Abstract: An assembly for a gas turbine engine includes a vane assembly having an inner platform and an airfoil section extending from the inner platform. A first combustor panel extends at least partially along the vane from upstream of the vane, and a blade outer air seal extends at least partially along the vane from downstream of the vane. The first combustor panel and the blade outer air seal define a platform gap located between a leading edge of the airfoil section of the vane and a trailing edge of the airfoil section of the vane.

公开(公告)号：US10422229B2

公开(公告)日：2019-09-24

申请号：US15465262

申请日：2017-03-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Carey Clum ,  Mark F. Zelesky

IPC: F01D5/18 ,  F01D5/14 ,  F02C3/04

Abstract: An airfoil may include an external airfoil surface and an airfoil body. The airfoil body may include an external wall structure and an internal wall structure. The external airfoil surface may be adjacent the external wall structure. The airfoil body may define a skin core that is at least partially defined by a first section of the external wall structure and a first section of the internal wall structure. The airfoil body may also define an embedded core that is at least partially defined by the first section of the internal wall structure. An embedded core heat transfer augmentation feature may be formed within the embedded core on an embedded core surface of the first section of the internal wall structure.

公开(公告)号：US10392958B2

公开(公告)日：2019-08-27

申请号：US14721223

申请日：2015-05-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Sergey Mironets ,  Edward F. Pietraszkiewicz ,  Alexander Staroselsky ,  Mark F. Zelesky

IPC: F01D11/12 ,  F01D5/14

Abstract: A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face.

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：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.

公开(公告)号：US10247419B2

公开(公告)日：2019-04-02

申请号：US15665837

申请日：2017-08-01

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Mark F. Zelesky ,  Andrew D. Burdick

IPC: F23R3/04 ,  F02C7/18 ,  F23R3/00 ,  F23R3/60 ,  F02C3/06 ,  F02K3/06

Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.