公开(公告)号：US10830054B2

公开(公告)日：2020-11-10

申请号：US16675879

申请日：2019-11-06

Applicant: United Technologies Corporation

Inventor： James T. Auxier ,  Parth Jariwala ,  Bret M. Teller

IPC: F01D5/18 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F23R3/00

Abstract: A casting core may comprise a tip flag material having a forward cavity and a first spear cavity disposed aft of the forward cavity. A trailing edge discharge material may be separated from the tip flag material and include a first row of cavities. The first row of cavities may comprise a first racetrack cavity. A second row of cavities may be disposed aft of the first row of cavities and include a second racetrack cavity. A third row of cavities may be disposed aft of the second row of cavities and include a circular cavity. A fourth row of cavities may be disposed aft of the third row of cavities and include a second spear cavity.

公开(公告)号：US10508552B2

公开(公告)日：2019-12-17

申请号：US15096243

申请日：2016-04-11

Applicant: United Technologies Corporation

Inventor： James T. Auxier ,  Parth Jariwala ,  Bret M. Teller

IPC: F01D5/18 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F23R3/00

Abstract: A casting core and/or an airfoil may comprise a tip flag cavity having a forward pedestal and a first spear pedestal disposed aft of the forward pedestal. A trailing edge discharge cavity may be separated from the tip flag cavity and include a first row of pedestals. The first row of pedestals may comprise a first racetrack pedestal. A second row of pedestals may be disposed aft of the first row of pedestals and include a second racetrack pedestal. A third row of pedestals may be disposed aft of the second row of pedestals and include a circular pedestal. A fourth row of pedestals may be disposed aft of the third row of pedestals and include a second spear pedestal.

公开(公告)号：US10408071B2

公开(公告)日：2019-09-10

申请号：US15022725

申请日：2014-08-26

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.

公开(公告)号：US09797260B2

公开(公告)日：2017-10-24

申请号：US14694416

申请日：2015-04-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Graham Ryan Philbrick ,  Ken Lagueux ,  Bret M. Teller

IPC: F01D5/18 ,  F01D5/20 ,  F01D11/08

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D5/20 ,  F01D11/08 ,  Y02T50/676

Abstract: A gas turbine engine component according to an exemplary aspect of this disclosure includes a peripheral portion defining an internal cooling passage and a recess in fluid communication with the internal cooling passage. The peripheral portion includes an outer wear surface, and the recess tapers toward the outer wear surface.

公开(公告)号：US20170211396A1

公开(公告)日：2017-07-27

申请号：US15143717

申请日：2016-05-02

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Parth Jariwala ,  Bret M. Teller ,  Mark F. Zelesky ,  James Tilsley Auxier

IPC: F01D5/18 ,  F04D29/58 ,  F04D29/32 ,  F04D29/54 ,  F01D9/02 ,  F01D25/12

CPC classification number: F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2260/606 ,  Y02T50/676

Abstract: An airfoil of a gas turbine engine is provided including a leading edge extending in a radial direction, a tip extending in an axial direction from the leading edge, a first rib extending radially within the airfoil, the leading edge and the first rib defining a leading edge cavity within the airfoil, a second rib, the second rib and the first rib defining a serpentine cavity therein, a third rib extending axially within the tip, a flag tip cavity defined by the third rib, the leading edge, and the tip, the leading edge cavity fluidly connected to the flag tip cavity, and a bypass aperture formed between the first rib and the third rib, the bypass aperture configured to fluidly connect the serpentine cavity with the flag tip cavity.

公开(公告)号：US20160090844A1

公开(公告)日：2016-03-31

申请号：US14686945

申请日：2015-04-15

Applicant: United Technologies Corporation

Inventor： James T. Auxier ,  Parth Jariwala ,  Mark F. Zelesky ,  Bret M. Teller

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  Y02T50/676

Abstract: A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side.

Abstract translation: 用于燃气涡轮发动机的部件包括提供压力和吸力侧的外表面。 部件中的冷却通道包括蛇形通道，该蛇形通道具有分别配置成在彼此相反的方向上提供流体流动的第一和第二通道。 第一遍包括相对于彼此嵌套并在厚度方向上重叠的第一和第二部分。 第一和第二部分通过共享一个共同的墙壁彼此相邻。 第一部分设置在吸力侧。 第二部分设置在压力侧。