公开(公告)号：US20190249568A1

公开(公告)日：2019-08-15

申请号：US16389193

申请日：2019-04-19

Applicant: United Technologies Corporation

Inventor： Matthew Budnick ,  Conway Chuong ,  Jonathan Ariel Scott ,  Darrell Weidner ,  Chris Bates

IPC: F01D25/14 ,  F01D25/16 ,  F01D25/24

CPC classification number: F01D25/145 ,  F01D25/162 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/60 ,  F05D2240/15 ,  F05D2260/231 ,  Y10T29/49321

Abstract: An assembly for a gas turbine engine includes a first casing, a second casing, and struts extending from the first casing to support the second casing. The assembly further includes a fairing and a multi-piece heat shield assembly. The fairing is disposed between the first casing and the second casing and around each of the struts. The multi-piece heat shield assembly includes a first shield extending between the first casing and the fairing, and a second shield extending between the fairing and the first casing. The multi-piece heat shield assembly further includes a third shield extending between the fairing and the second casing, and fourth and fifth heat shields extending from the third heat shield between the fairing and each of the struts.

公开(公告)号：US10329956B2

公开(公告)日：2019-06-25

申请号：US14758382

申请日：2013-12-19

Applicant: United Technologies Corporation

Inventor： Jonathan Ariel Scott

IPC: F01D25/24 ,  F01D25/30 ,  F01D9/06

Abstract: A turbine exhaust case frame (100) comprises an inner ring (104), an outer ring (102), and a plurality of load-bearing struts (106). The inner ring is configured to carry load from inner bearings. The outer ring features a multi-function boss (116) with a service line aperture (124) and a mounting point for the turbine exhaust case. The load-bearing struts connect the inner ring to the outer ring, and have a service line passage (128) extending from the service line aperture to the inner ring.

公开(公告)号：US10240532B2

公开(公告)日：2019-03-26

申请号：US14655656

申请日：2013-12-20

Applicant: United Technologies Corporation

Inventor： Jonathan Ariel Scott ,  William Yeager

IPC: F02C7/20 ,  F02C7/12 ,  F01D9/06 ,  F01D25/16

Abstract: A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts; and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a film cooling hole formed through the frame proximate the outer frame junction.

公开(公告)号：US10240481B2

公开(公告)日：2019-03-26

申请号：US14758267

申请日：2013-12-19

Applicant: United Technologies Corporation

Inventor： Jonathan Ariel Scott ,  Conway Chuong

IPC: F01D9/06 ,  F01D25/14 ,  F01D25/24

Abstract: A fairing (118) comprises an inner platform (122), an outer platform (120), a plurality of vane bodies (124), and a flange (126). The inner and outer rings define radially inner and outer boundaries of an airflow path. The vane bodies extend radially from the inner platform to the outer platform. The flange extends radially outward from the outer platform, and is defined by a frustoconical surface (S) extending radially inward and axially aft from a substantially radial upstream surface.

公开(公告)号：US10053998B2

公开(公告)日：2018-08-21

申请号：US14653243

申请日：2013-12-23

Applicant: United Technologies Corporation

Inventor： Tuan David Vo ,  Conway Chuong ,  Matthew Budnick ,  Jonathan Ariel Scott

IPC: F01D11/02 ,  F01D11/12 ,  F01D25/28 ,  F02C7/28 ,  F01D9/06 ,  F01D11/00 ,  F01D25/16

CPC classification number: F01D11/02 ,  F01D9/065 ,  F01D11/001 ,  F01D11/122 ,  F01D25/162 ,  F01D25/28 ,  F02C7/28

Abstract: A gas turbine engine assembly includes a first module, a second module rotatable about a center line of the gas turbine engine and fluidly coupled with the first module, and a multi-purpose seal support. The multi-purpose seal support includes an aft end secured to the first module, and a forward end disposed proximate the second module. The forward end has a discourager portion, a seal portion, and a meshing portion.

公开(公告)号：US09982567B2

公开(公告)日：2018-05-29

申请号：US14958984

申请日：2015-12-04

Applicant: United Technologies Corporation

Inventor： Jonathan Ariel Scott ,  Steven J. Bauer

IPC: F01D25/08 ,  F01D25/28 ,  F02C7/20 ,  F01D9/06

CPC classification number: F01D25/28 ,  F01D9/065 ,  F02C7/20 ,  F05D2220/32 ,  F05D2260/31

Abstract: A gas turbine engine mid-turbine frame includes an annular case that has a hole. A tie rod with a first end extends through the hole. The first end includes a threaded portion. A nut is secured to the threaded portion to clamp the tie rod to the annular case. A tab washer is arranged between the nut and the annular case. The tab washer interlocks the nut to the case to prevent relative rotation therebetween.

公开(公告)号：US09903224B2

公开(公告)日：2018-02-27

申请号：US14655644

申请日：2013-12-18

Applicant: United Technologies Corporation

Inventor： Jonathan Ariel Scott ,  Larry B. Hawke

IPC: F01D25/12 ,  F01D25/30 ,  F01D25/24 ,  F01D25/16 ,  F01D9/06 ,  F02C7/20 ,  F02C7/12

CPC classification number: F01D25/125 ,  F01D9/065 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F02C7/12 ,  F02C7/20 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/675

Abstract: A gas turbine module comprises a frame, a bearing support ring, a service line, and a scupper channel system. A service line is disposed through a radial passage of the frame and a service line port of the bearing support ring. The scupper line is disposed radially through a radial passage of the frame and is open to the scupper drain port. The scupper channel system is formed into a radially inner surface of the bearing support ring, and includes a collection portion in fluid communication with the scupper drain port.

公开(公告)号：US20150354411A1

公开(公告)日：2015-12-10

申请号：US14758273

申请日：2013-12-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ariel Scott

IPC: F01D25/28 ,  F01D25/30 ,  F01D25/24

CPC classification number: F01D25/28 ,  F01D25/24 ,  F01D25/30 ,  Y10T29/49323

Abstract: A turbine exhaust case (28) comprises a one-piece fairing (120) defining an air-flow path through the turbine exhaust case, and a multi-piece frame (100). The multi-piece frame is disposed through and around the one-piece vane fairing to support a bearing load, and comprises an inner ring (104), an outer ring (102), a plurality of covers (110), and a plurality of radial struts (106). The outer ring is disposed concentrically outward of the inner ring, and has hollow bosses (114) with strut apertures (SA) at vane locations. The covers are secured to the hollow bosses. The radial struts pass through the one-piece vane fairing and through apertures in the outer angled ring, and are radially fastened to the inner ring and the flat caps.

Abstract translation: 涡轮机排气箱（28）包括限定通过涡轮排气箱的空气流动路径的一体式整流罩（120）和多件式框架（100）。 多件式框架布置在整体式叶片整流罩周围并支撑轴承负载，并包括内圈（104），外圈（102），多个盖（110）和多个 径向支柱（106）。 外环同心地设置在内圈的外侧，并且在叶片位置具有带有支柱孔（SA）的中空凸台（114）。 盖被固定到中空的凸台上。 径向支柱穿过单片叶片整流罩并穿过外角形环中的孔，并径向固定在内环和平盖上。

公开(公告)号：US20150337683A1

公开(公告)日：2015-11-26

申请号：US14758267

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ariel Scott ,  Conway Chuong

IPC: F01D25/14 ,  F01D25/24

CPC classification number: F01D25/14 ,  F01D9/065 ,  F01D25/24 ,  F01D25/243

Abstract: A fairing (118) comprises an inner platform (122), an outer platform (120), a plurality of vane bodies (124), and a flange (126). The inner and outer rings define radially inner and outer boundaries of an airflow path. The vane bodies extend radially from the inner platform to the outer platform. The flange extends radially outward from the outer platform, and is defined by a frustoconical surface (S) extending radially inward and axially aft from a substantially radial upstream surface.

Abstract translation: 整流罩（118）包括内平台（122），外平台（120），多个叶片体（124）和凸缘（126）。 内环和外环限定了气流路径的径向内部和外部边界。 叶片体从内平台径向延伸到外平台。 凸缘从外平台径向向外延伸，并且由从基本上径向的上游表面径向向内和轴向延伸的截头圆锥形表面（S）限定。

公开(公告)号：US20150330250A1

公开(公告)日：2015-11-19

申请号：US14758367

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ariel Scott ,  Albert Veninger

IPC: F01D25/14 ,  F01D9/02 ,  F01D25/12 ,  F01D25/00 ,  F01D25/30 ,  F01D25/24

CPC classification number: F01D25/145 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/005 ,  F01D25/12 ,  F01D25/125 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/231 ,  Y02T50/673 ,  Y02T50/675

Abstract: A turbine exhaust case (28) for a gas turbine engine (10) comprises a frame (100), a vane fairing (108), a heat shield (124, 126, 128), and a serpentine cooling path. The frame has an outer ring (102) and an inner ring (104) connected by a hollow strut (106) with a radial service line passage (132). The vane fairing is disposed between the inner ring and the outer ring to define a core airflow path. The heat shield is disposed between the vane fairing and the frame. The serpentine cooling flow path passes through and around the outer ring, the inner ring, and the plurality of struts

Abstract translation: 用于燃气涡轮发动机（10）的涡轮机排气箱（28）包括框架（100），叶片整流罩（108），隔热罩（124,126,128）和蛇形冷却路径。 框架具有通过中空支柱（106）与径向服务线通道（132）连接的外环（102）和内环（104）。 叶片整流罩设置在内环和外圈之间以限定芯气流路径。 隔热罩设置在叶片整流罩和框架之间。 蛇形冷却流路穿过外环，内环和多个支柱