公开(公告)号：US10428660B2

公开(公告)日：2019-10-01

申请号：US15420882

申请日：2017-01-31

Applicant: United Technologies Corporation

Inventor： James D Hill ,  Ram Ranjan ,  Glenn Levasseur

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

Abstract: An airfoil may comprise an airfoil body having a leading edge and a trailing edge. A heat pipe may be disposed within the airfoil. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be disposed within the airfoil body and may be configured to remove heat from the trailing edge. The second cooling apparatus may be disposed within the airfoil body and may be configured to remove heat from the leading edge.

公开(公告)号：US20150354389A1

公开(公告)日：2015-12-10

申请号：US14730400

申请日：2015-06-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David R Pack ,  Julian Partyka ,  James D Hill ,  Gabriel L Suciu ,  Gregory M Dolansky ,  Brian D Merry

IPC: F01D11/00 ,  F01D5/06

CPC classification number: F01D11/008 ,  F01D5/06 ,  F01D11/001 ,  F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  Y02T50/671

Abstract: A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.

Abstract translation: 用于燃气涡轮发动机的密封段包括在第一径向跨度和第二径向跨度之间延伸的第一轴向跨度。 第二轴向跨度在第一径向跨度和第二径向跨度之间延伸，第一径向跨度，第二径向跨度，第一轴向跨度和第二轴向跨度形成扭矩箱。

公开(公告)号：US10167723B2

公开(公告)日：2019-01-01

申请号：US14729473

申请日：2015-06-03

Applicant: United Technologies Corporation

Inventor： Gabriel L Suciu ,  Brian D Merry ,  James D Hill

IPC: F01D5/08 ,  F02C3/04 ,  F02C3/14 ,  F01D11/00 ,  F01D11/02 ,  F01D25/12 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28

Abstract: A gas turbine engine includes a turbine section fluidly connected to a combustor by a primary flow path. The turbine section includes a first portion at a high pressure relative to a second portion. A thermally isolated cooling plenum is positioned radially inward of the primary flow path. The cooling plenum is defined by a forward wall, a shaft structure, an aft wall, and an inner diameter wall of the primary flow path. Air in the thermally isolated cooling plenum is thermally isolated from air in the primary flow path. At least one cooling air system is operable to provide cooling air to the thermally isolated cooling plenum.

公开(公告)号：US10179377B2

公开(公告)日：2019-01-15

申请号：US14775964

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L Suciu ,  Gopal Das ,  Ioannis Alvanos ,  Brian D Merry ,  James D Hill ,  Allan R Penda

IPC: B23K26/342 ,  B22F3/105 ,  B22F5/00 ,  C22C1/04 ,  B33Y10/00

Abstract: A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique.

公开(公告)号：US10018360B2

公开(公告)日：2018-07-10

申请号：US14728991

申请日：2015-06-02

Applicant: United Technologies Corporation

Inventor： Gabriel L Suciu ,  Brian D Merry ,  James D Hill

IPC: F02C6/08 ,  F23R3/10 ,  F02C3/04 ,  F01D5/08 ,  F01D9/06 ,  F01D25/12 ,  F02C7/18

CPC classification number: F23R3/10 ,  F01D5/082 ,  F01D9/06 ,  F01D25/125 ,  F02C3/04 ,  F02C6/08 ,  F02C7/185 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/303 ,  F05D2270/3062 ,  Y02T50/676

Abstract: A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system.

公开(公告)号：US10001061B2

公开(公告)日：2018-06-19

申请号：US14732319

申请日：2015-06-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L Suciu ,  Brian D Merry ,  James D Hill

IPC: F01D5/08 ,  F02C7/18

CPC classification number: F02C7/18 ,  F01D5/085

Abstract: A cooling system for gas turbine engines includes a turbine rotor compartment defining a cooling air plenum. A plurality of turbine discs are rotatably housed within the rotor compartment. A cooling air inlet is in fluid communication with the plenum. Each turbine disc includes a cooling outlet in fluid communication with the plenum for cooling the rotor compartment.