公开(公告)号：US20160153291A1

公开(公告)日：2016-06-02

申请号：US14811122

申请日：2015-07-28

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Michael G. McCaffrey ,  Thomas N. Slavens

IPC: F01D9/02 ,  F02C7/18

CPC classification number: F01D9/023 ,  F01D5/08 ,  F01D5/081 ,  F01D5/082 ,  F01D9/065 ,  F01D17/162 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/232 ,  Y02T50/673 ,  Y02T50/676

Abstract: A cooling system integrated into a stator assembly of a gas turbine engine has an on-board injector or cooling nozzle located for cooling of a rotor assembly. The nozzle may be generally annular and may contain a plurality of pivoting airfoils circumferentially spaced from one-another for directing cooling air flow from the nozzle and generally toward a plurality of holes in a cover of the rotor assembly. The pivoting airfoils are adapted to move between a spoiled state where the mass flow of cooling air is reduced, and to an optimal state where the mass flow is increased. The system may further include a plurality of fixed airfoils in the nozzle with adjacent fixed airfoils defining a discharge orifice in the nozzle. Each one of the plurality of pivoting airfoils may be located in a respective discharge orifice.

Abstract translation: 集成到燃气涡轮发动机的定子组件中的冷却系统具有用于冷却转子组件的车载喷射器或冷却喷嘴。 喷嘴可以是大致环形的，并且可以包含多个相互间隔开的旋转翼型件，用于引导来自喷嘴的冷却空气流并且大致朝向转子组件的盖中的多个孔。 旋转翼型件适于在冷却空气的质量流量减小的损坏状态和质量流量增加的最佳状态之间移动。 该系统还可以包括在喷嘴中的多个固定翼型件，其中相邻的固定翼型件在喷嘴中限定排放孔口。 多个枢转翼型件中的每一个可以位于相应的排放口中。

公开(公告)号：US20160076451A1

公开(公告)日：2016-03-17

申请号：US14827050

申请日：2015-08-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John McBrien ,  Thomas N. Slavens ,  Clifford J. Musto ,  Timothy J. Jennings ,  Nicholas M. LoRicco ,  Sasha M. Moore

IPC: F02C7/18 ,  F01D9/02 ,  F02C3/04 ,  F01D5/18

CPC classification number: F02C7/18 ,  F01D5/186 ,  F01D9/023 ,  F01D9/065 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser.

Abstract translation: 描述燃气涡轮发动机部件。 该部件包括具有与冷却剂流相邻的内表面和与气流相邻的外表面的部件壁。 部件壁包括具有由内表面限定的入口和由外表面限定的出口的冷却孔。 冷却孔还具有冷却孔的横截面积最小的计量位置，位于入口和计量位置之间的内部扩散器，内部扩散器的堆积分流器部分和内部扩散器的蓄压器部分。

公开(公告)号：US20150322860A1

公开(公告)日：2015-11-12

申请号：US14706033

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F02C7/12 ,  F01D25/12 ,  F01D9/04

CPC classification number: F02C7/12 ,  F01D9/02 ,  F01D9/041 ,  F01D25/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/20 ,  F05D2260/201 ,  Y02T50/676

Abstract: A variable vane pack includes an inner platform, an outer platform, radially outward of the inner platform, a plurality of vanes connecting the inner platform to the outer platform, wherein the outer platform comprises a platform body and an impingement plate, the impingement plate having a radially inward impingement plate, a radially outward pressure distribution plate, and an impingement plenum defined between the radially inward impingement plate and the radially outward pressure distribution plate.

Abstract translation: 可变叶片组包括内平台，内平台径向外侧的外平台，将内平台连接到外平台的多个叶片，其中外平台包括平台本体和冲击板，冲击板具有 径向向内的冲击板，径向向外的分配板和限定在径向向内的冲击板和径向向外的分配板之间的冲击气室。

公开(公告)号：US11059093B2

公开(公告)日：2021-07-13

申请号：US16217908

申请日：2018-12-12

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  James Tilsley Auxier

IPC: B22C9/10 ,  B22F7/08 ,  B33Y10/00 ,  B33Y80/00 ,  B22D23/06 ,  B22D27/04 ,  B22F5/00 ,  B22F10/20 ,  C30B1/02 ,  B28B1/00 ,  B28B7/34

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.

公开(公告)号：US10830096B2

公开(公告)日：2020-11-10

申请号：US14917434

申请日：2014-09-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Steven Bruce Gautschi

IPC: F01D25/12 ,  F01D17/16 ,  F01D5/18 ,  F01D9/04 ,  F01D17/14 ,  F01D25/16

Abstract: A pivoting turbine vane has an airfoil, an inner bearing race and an outer bearing race, with the inner and outer bearing races on a pivot axis of the pivoting turbine vane. There are cooling air passages through at least one of the inner and outer bearing races to provide cooling air from a remote facing face of at least one of the inner and outer bearing races to an airfoil facing face of at least one of the inner and outer bearing races. A turbine section is also disclosed.

公开(公告)号：US20200256196A1

公开(公告)日：2020-08-13

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：US10731482B2

公开(公告)日：2020-08-04

申请号：US14959057

申请日：2015-12-04

Applicant: United Technologies Corporation

Inventor： Mosheshe Camara-Khary Blake ,  Thomas N. Slavens ,  John R. Farris

IPC: F01D5/28 ,  F01D11/12 ,  F01D9/04 ,  F01D11/08 ,  F01D25/08 ,  F01D25/24 ,  F02C3/04 ,  F02C7/00

Abstract: A gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a plurality of gas path components exposed to a primary fluid flowpath through the compressor section, the combustor section and the turbine section. At least one of the gas path components includes an exterior facing surface, a lattice structure extending outward from the exterior facing surface, the lattice structure being integral to the exterior facing surface, and a thermal barrier coating adhered to at least a portion of the exterior facing surface and the lattice structure.

公开(公告)号：US10465607B2

公开(公告)日：2019-11-05

申请号：US15479747

申请日：2017-04-05

Applicant: United Technologies Corporation

Inventor： Kevin L. Zacchera ,  Thomas N. Slavens

IPC: F23R3/00 ,  F02C7/18 ,  C23C14/04 ,  F01D5/18 ,  F01D5/28 ,  C23C4/01

Abstract: A method for applying a coating to a substrate having a plurality of holes. The method comprises: applying a braze material to a substrate having a plurality of holes; heating the substrate to melt the braze material to form a melt; cooling the substrate to solidify the melt to form plugs in the respective holes; applying a coating to the substrate; and further heating the substrate to melt the plugs.

公开(公告)号：US10436039B2

公开(公告)日：2019-10-08

申请号：US15032736

申请日：2014-10-10

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Thomas N. Slavens

IPC: F01D5/18 ,  F01D5/20 ,  B22F3/105 ,  B22F5/04 ,  B22F7/08 ,  B23K26/342 ,  B22D25/02 ,  B23K15/00 ,  B33Y10/00 ,  B33Y80/00

Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.

公开(公告)号：US10364041B2

公开(公告)日：2019-07-30

申请号：US15218915

申请日：2016-07-25

Applicant: United Technologies Corporation

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

IPC: B64D41/00 ,  F04D17/10 ,  F02C3/08 ,  F02C3/14

Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.