公开(公告)号：US20170051628A1

公开(公告)日：2017-02-23

申请号：US14827889

申请日：2015-08-17

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Carey Clum

IPC: F01D17/10 ,  F01D25/12 ,  F01D5/18 ,  F01D25/10

CPC classification number: F01D17/105 ,  F01D5/18 ,  F01D25/10 ,  F01D25/12 ,  F02C7/185 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/3013 ,  F05D2270/3015

Abstract: A conduit system for a gas turbine engine includes, a heat exchanger configured to cool fluid flowing therethrough having an inlet and an outlet, at least one by-pass in operable communication with the heat exchanger that is configured to allow fluid to exit the heat exchanger before reaching the outlet, and a conduit that is in fluidic communication with the outlet and the at least one by-pass.

Abstract translation: 用于燃气涡轮发动机的管道系统包括：热交换器，其构造成冷却流过其中的流体具有入口和出口，至少一个旁路与热交换器可操作地连通，该热交换器构造成允许流体离开热交换器 在到达出口之前，以及与出口和至少一个旁路流体连通的导管。

公开(公告)号：US20150345302A1

公开(公告)日：2015-12-03

申请号：US14706045

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Michael J. Birnkrant ,  Dominic J. Mongillo, JR. ,  Joel H. Wagner ,  Weina Li ,  Jose L. Santana ,  Carey Clum ,  James T. Beals

IPC: F01D5/18

CPC classification number: F01D5/183 ,  C04B35/01 ,  C04B35/10 ,  C04B35/453 ,  C04B35/56 ,  C04B35/565 ,  C04B35/58 ,  C04B35/58085 ,  C04B38/00 ,  C04B38/0054 ,  C04B38/0074 ,  C04B2111/00982 ,  C04B2111/763 ,  F05D2260/203 ,  F05D2300/10 ,  F05D2300/20 ,  F05D2300/514 ,  F05D2300/612 ,  Y02T50/676 ,  C04B38/0045

Abstract: A transpiration-cooled article includes a body wall that has first and second opposed surfaces. The first surface is adjacent a passage that is configured to receive a pressurized cooling fluid. At least a portion of the body wall includes a nanocellular foam through which the pressurized cooling fluid from the passage can flow to the second surface. The article can be an airfoil that includes an airfoil body that has an internal passage and an outer gas-path surface. At least a portion of the airfoil body includes a nanocellular foam through which cooling fluid from the internal passage can flow to the gas-path surface.

Abstract translation: 蒸发冷却制品包括具有第一和第二相对表面的主体壁。 第一表面邻近经配置以接收加压冷却流体的通道。 体壁的至少一部分包括纳米细胞泡沫，来自通道的加压冷却流体可以通过该泡沫泡沫流到第二表面。 该制品可以是包括具有内部通道和外部气体路径表面的翼型件的翼型件。 翼型体的至少一部分包括纳米孔泡沫，通过该纳米孔泡沫，来自内部通道的冷却流体可通过其流到气体路径表面。

公开(公告)号：US11274559B2

公开(公告)日：2022-03-15

申请号：US16743435

申请日：2020-01-15

Applicant: United Technologies Corporation

Inventor： Robin Prenter ,  Timothy J. Jennings ,  Carey Clum

IPC: F01D5/18 ,  F02C7/30

Abstract: A gaspath component for a gas turbine engine includes a platform. A body extends outward from the platform and includes at least one internal cooling passage. The internal cooling passage includes at least one particulate redirection feature defined at an end of the body opposite the platform. The at least one particulate redirection feature includes a first face oblique to and facing an expected flow of fluid through the internal cooling passage and defines at least one corresponding opening.

公开(公告)号：US11098899B2

公开(公告)日：2021-08-24

申请号：US15903592

申请日：2018-02-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Carey Clum ,  Dennis M Moura

IPC: F23R3/00

Abstract: A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.

公开(公告)号：US10890074B2

公开(公告)日：2021-01-12

申请号：US15968043

申请日：2018-05-01

Applicant: United Technologies Corporation

Inventor： Timothy J. Jennings ,  Carey Clum

IPC: F01D5/18

Abstract: A gas turbine engine component includes an airfoil that has pressure and suction side walls that extend in a chord-wise direction between a leading edge and a trailing edge. The pressure and suction side walls extend in a radial direction between a platform and a tip to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction side walls and has a first passage along the pressure side wall and a second passage along the suction side wall. The first passage is configured to receive cooling air from a cooling air source. The second passage is configured to receive cooling air from the first passage near the tip. A platform passage is arranged in the platform and is configured to purge the cooling air from the second passage near the trailing edge.

公开(公告)号：US10815800B2

公开(公告)日：2020-10-27

申请号：US15368829

申请日：2016-12-05

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo, Jr.

IPC: F01D5/20 ,  F01D9/04 ,  F01D5/18

Abstract: An airfoil includes an airfoil body having a first wall, a second wall, a third wall, a tip surface, and a rib. The first wall radially extends between a root region and a tip region and axially extends between a leading edge and a trailing edge. The second wall radially extends from the tip region towards the root region and axially extends between the leading edge and the trailing edge. The third wall radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge. The tip surface circumferentially extends between the second wall and the third wall. The rib is radially spaced apart from the tip surface and circumferentially extends between the first wall and the third wall.

公开(公告)号：US20200291791A1

公开(公告)日：2020-09-17

申请号：US16811249

申请日：2020-03-06

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  B22C9/10 ,  B22C9/24 ,  F01D9/06

Abstract: Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.

公开(公告)号：US20200277861A1

公开(公告)日：2020-09-03

申请号：US16739254

申请日：2020-01-10

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Carey Clum ,  Matthew A. Devore

IPC: F01D5/18 ,  F01D9/06 ,  F02C7/18

Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span. A method of manufacturing a gas turbine engine component and a method of controlling flow in a gas turbine engine component are also disclosed.

公开(公告)号：US10648345B2

公开(公告)日：2020-05-12

申请号：US15832467

申请日：2017-12-05

Applicant: United Technologies Corporation

Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, Jr.

IPC: F01D5/18 ,  F02C9/18 ,  F02C3/04

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. The resupply hole has a single inlet that is fluidly connected to multiple discrete outlet apertures. A centerline of the single inlet is arranged at an angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.

公开(公告)号：US20190338646A1

公开(公告)日：2019-11-07

申请号：US15967950

申请日：2018-05-01

Applicant: United Technologies Corporation

Inventor： Timothy J. Jennings ,  Carey Clum

IPC: F01D5/18

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between a leading edge and a trailing edge. The pressure and suction side walls extend in a radial direction between a platform and a tip to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction side walls and has a first passage along the pressure side wall and a second passage along the suction side wall. The first passage is configured to receive cooling air from a cooling air source radially inward of the platform. The second passage is configured to receive cooling air from the first passage near the tip. A root flag passage is configured to purge the cooling air from the second passage near the trailing edge.