公开(公告)号：US10794214B2

公开(公告)日：2020-10-06

申请号：US15589009

申请日：2017-05-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Mark F. Zelesky ,  Ioannis Alvanos ,  Brian Merry

IPC: F01D11/24 ,  F01D25/24

Abstract: A clearance control system for a gas turbine engine comprises at least one case support associated with an engine case defining an engine center axis. A clearance control ring is positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring. The clearance control ring includes a first mount feature. An outer air seal has a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature. An injection source inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.

公开(公告)号：US20200276637A1

公开(公告)日：2020-09-03

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: B22D25/02 ,  B22C3/00 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/12 ,  B22C9/24 ,  B22D29/00 ,  B22F3/10 ,  B22F3/24 ,  B22F7/04 ,  B23K1/00 ,  B23K1/19

Abstract: A method of 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：US20200271013A1

公开(公告)日：2020-08-27

申请号：US16285820

申请日：2019-02-26

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky

IPC: F01D25/12 ,  F01D25/16 ,  F01D25/18 ,  F16C33/72 ,  F16C37/00

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal plate includes a cooling passageway having a circumferentially-extending section radially aligned with the contact area.

公开(公告)号：US10690346B2

公开(公告)日：2020-06-23

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 ,  F23R3/60 ,  F23R3/06 ,  F16B43/00

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：US10556269B1

公开(公告)日：2020-02-11

申请号：US15473403

申请日：2017-03-29

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

Abstract: A method of making a refractory metal core includes forming two layers of the core out of a material. The layers are bonded together to form a laminate master pattern, and a flexible mold is formed around the pattern. The pattern is removed from the flexible mold, and pulverulent refractory metal material is poured into the flexible mold. The pulverulent refractory metal material is sintered to form the refractory metal core.

公开(公告)号：US10513932B2

公开(公告)日：2019-12-24

申请号：US15200063

申请日：2016-07-01

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Eleanor D. Kaufman

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C3/10

Abstract: A turbine engine airfoil includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.

公开(公告)号：US20190383153A1

公开(公告)日：2019-12-19

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

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：US20180334909A1

公开(公告)日：2018-11-22

申请号：US16048466

申请日：2018-07-30

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Joel H. Wagner ,  Thomas N. Slavens

IPC: F01D5/18 ,  F23R3/00 ,  B22F3/105 ,  B23P15/26 ,  F01D5/14 ,  F02C7/18 ,  F01D25/24 ,  F01D25/12 ,  F01D25/08 ,  F01D11/08 ,  F01D9/02 ,  B33Y80/00 ,  B33Y70/00 ,  B33Y10/00

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.

公开(公告)号：US10126175B2

公开(公告)日：2018-11-13

申请号：US14564774

申请日：2014-12-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Charles W. Haldeman ,  Andrew Consiglio ,  Mark F. Zelesky ,  Joel H. Wagner

IPC: G01J5/00 ,  G01K1/00 ,  F01D21/00 ,  F01D5/28 ,  F01D21/12

Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.

公开(公告)号：US20180320548A1

公开(公告)日：2018-11-08

申请号：US16033356

申请日：2018-07-12

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D25/12 ,  F28F7/02 ,  F28F1/40 ,  F01D25/10 ,  F28D15/00 ,  F02C7/14 ,  F28F1/12

CPC classification number: F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/232 ,  F28D15/00 ,  F28F1/124 ,  F28F1/40 ,  F28F7/02 ,  F28F2255/18 ,  Y02T50/676

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.