公开(公告)号：WO2014133648A2

公开(公告)日：2014-09-04

申请号：PCT/US2013/075422

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： CHUONG, Conway ,  BUDNICK, Matthew

CPC classification number: F01D25/246 ,  F01D25/162 ,  F05D2260/201 ,  Y02T50/675

Abstract: An assembly includes a gas turbine engine component and a plate. The plate is spaced from a surface of the component and generally conforms to the shape of the surface. The plate and component form a passageway that allows for passage of a secondary gas flow between the component and the plate.

Abstract translation: 组件包括燃气涡轮发动机部件和板。 该板与部件的表面间隔开并且大致与表面的形状一致。 板和部件形成允许在部件和板之间通过辅助气流的通道。

公开(公告)号：WO2014105781A1

公开(公告)日：2014-07-03

申请号：PCT/US2013/077399

申请日：2013-12-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BUDNICK, Matthew

IPC: F01D25/14 ,  F02C7/12

CPC classification number: F01D25/14 ,  F01D25/12 ,  F01D25/162 ,  F01D25/28 ,  F02C7/12 ,  F02C7/20 ,  F05D2220/32 ,  F05D2260/202 ,  Y02T50/675

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 plurality of film cooling holes formed through a circumferentially facing wall of each strut at a location distal from the outer frame junction.

Abstract translation: 用于燃气涡轮发动机的模块包括框架和框架冷却系统。 框架包括周向分布的多个径向延伸的支柱。 每个支柱在外框架接合处连接到外框架部分，并且在内框架结处连接到内框架部分。 框架冷却系统包括入口，从入口径向延伸穿过多个框架支柱中的每一个的多个冷却空气通道和出口。 出口与至少一个冷却空气通道流体连通，并且包括多个薄膜冷却孔，该多个薄膜冷却孔通过远离外框架结的位置穿过每个支柱的周向面向的壁。

公开(公告)号：WO2014105573A1

公开(公告)日：2014-07-03

申请号：PCT/US2013/076169

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： YEAGER, William ,  CHUONG, Conway ,  BUDNICK, Matthew

IPC: F01D25/30 ,  F01D25/24 ,  F02C7/20

CPC classification number: F01D25/14 ,  F01D9/041 ,  F01D9/065 ,  F01D25/162 ,  F01D25/30 ,  F02C7/18 ,  F05D2240/15 ,  Y02T50/675

Abstract: A turbine exhaust case employed in an industrial gas turbine engine includes a frame, a fairing and a heat shield. The frame includes an outer ring, an inner ring, and struts connected between the outer ring and the inner ring. The fairing includes a fairing outer ring, a fairing inner ring, and fairing struts connected between the fairing outer ring and the fairing inner ring. The heat shield is located between the frame outer ring and the fairing outer ring and provides a thermal barrier between the fairing outer ring and the frame outer ring, wherein the heat shield includes an aft portion having a flange that interfaces with the frame outer ring to form an air dam that directs cooling airflow forward along the frame outer ring within an outer diameter cavity formed between the frame outer ring and the heat shield.

Abstract translation: 在工业燃气涡轮发动机中使用的涡轮机排气箱包括框架，整流罩和隔热罩。 框架包括外环和内圈以及连接在外圈和内圈之间的支柱。 整流罩包括整流罩外圈，整流罩内圈和连接在整流罩外圈和整流罩内圈之间的整流罩支柱。 隔热罩位于框架外圈和整流罩外圈之间，并且在整流罩外圈和框架外圈之间提供隔热罩，其中隔热罩包括具有凸缘的后部，该凸缘与框架外圈 在形成在框架外圈和隔热罩之间的外径腔内形成一个空气坝，该空气坝沿着框架外环向前引导冷却气流。

公开(公告)号：WO2014105658A1

公开(公告)日：2014-07-03

申请号：PCT/US2013/076761

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： CHUONG, Conway ,  BUDNICK, Matthew

IPC: F02C7/20 ,  F01D25/28

CPC classification number: F02C7/28 ,  F01D9/02 ,  F01D11/005 ,  F01D25/162 ,  F01D25/28 ,  F05D2240/55

Abstract: An assembly for a gas turbine engine includes a component, a fairing, and a seal. The fairing is disposed adjacent to the component and defines a primary gas flow path. The fairing has a rib that is located outside of the primary flow path and extends from an outer surface of the fairing. The seal is disposed between the rib and the component.

Abstract translation: 用于燃气涡轮发动机的组件包括部件，整流罩和密封件。 整流罩靠近部件设置并限定主要气体流动路径。 整流罩具有位于主流路外部并从整流罩的外表面延伸的肋。 密封件设置在肋和部件之间。

公开(公告)号：WO2014105512A1

公开(公告)日：2014-07-03

申请号：PCT/US2013/075632

申请日：2013-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BUDNICK, Matthew ,  CHUONG, Conway ,  SCOTT, Jonathan A.

IPC: F02C7/20 ,  F02C7/24 ,  F01D25/28

CPC classification number: F01D9/041 ,  F01D25/145 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F01D25/28 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2260/231 ,  F05D2260/30 ,  F05D2260/31

Abstract: A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.

Abstract translation: 涡轮机排气箱包括框架，整流罩，隔热罩和机械连杆。 框架包括外圈，内圈和连接外环和内圈的多个支柱。 整流罩包括设置在框架内的环形支撑结构。 隔热罩设置在框架和整流罩之间。 机械连接将隔热罩连接到整流罩。 在一个实施例中，隔热罩包括防止框架和整流罩之间的热传递的多件式隔热罩。 在各种实施例中，机械联动装置包括用于将隔热罩连接到整流罩的滑动接头或固定接头。

公开(公告)号：WO2014105492A1

公开(公告)日：2014-07-03

申请号：PCT/US2013/075449

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： CHUONG, Conway ,  BUDNICK, Matthew

IPC: F01D25/12 ,  F02C7/12

CPC classification number: F02C7/20 ,  F01D11/14 ,  F01D25/12 ,  F01D25/162 ,  F01D25/243 ,  F01D25/265 ,  F01D25/28 ,  Y02T50/675

Abstract: An annular mount for a gas turbine engine includes a first flange and a second flange. The first flange has an arcuate shape, and the second flange extends from the first flange. The second flange has an interface surface along at least one side and has a plurality of mounting apertures extending therethrough. The channels extend along a length of the interface surface from a first edge to a second edge.

Abstract translation: 用于燃气涡轮发动机的环形安装件包括第一凸缘和第二凸缘。 第一凸缘具有弓形形状，第二凸缘从第一凸缘延伸。 第二凸缘具有沿着至少一个侧面的界面，并具有贯穿其中的多个安装孔。 通道沿着接口表面的长度从第一边缘延伸到第二边缘。

公开(公告)号：WO2014105100A1

公开(公告)日：2014-07-03

申请号：PCT/US2013/022700

申请日：2013-01-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BUDNICK, Matthew

IPC: F01D11/00

CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D25/30

Abstract: A turbine seal system comprises a structural frame, a structural member, a seal and a bumper. The structural member is disposed opposite the structural frame. The seal extends between the structural frame and the structural member. The bumper is anchored to the structural frame or the structural member and extends toward a mid-region of the seal. In one embodiment, the structural frame comprises a ring-strut-ring turbine exhaust case.

Abstract translation: 涡轮密封系统包括结构框架，结构构件，密封件和保险杠。 结构构件与结构框架相对设置。 密封件在结构框架和结构构件之间延伸。 保险杠固定在结构框架或结构构件上并延伸到密封件的中间区域。 在一个实施例中，结构框架包括环形支撑环涡轮机排气箱。

公开(公告)号：WO2015020775A1

公开(公告)日：2015-02-12

申请号：PCT/US2014/047144

申请日：2014-07-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BUDNICK, Matthew ,  CHUONG, Conway

IPC: F01D11/00 ,  F02C7/28

CPC classification number: F01D11/005 ,  F01D11/001 ,  F01D15/10 ,  F01D25/24 ,  F02C7/28 ,  F05D2220/30 ,  F05D2220/76 ,  F05D2240/55

Abstract: A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path surface of a flow path extending in an axial direction. A seal plate has first and second ends radially spaced from one another with respect to the axial direction. The first end is operatively secured to the engine static structure. The second end is configured to seal relative to the fairing. The seal plate includes a portion between the first and second ends that extends substantially in the axial direction and configured to permit the second end to move away from the fairing in the axial direction relative to the first end in response to thermal growth.

Abstract translation: 燃气涡轮发动机包括发动机静止结构。 整流罩相对于发动机静态结构被支撑并且构造成提供沿轴向延伸的流动路径的流路表面。 密封板具有相对于轴向方向彼此径向间隔开的第一和第二端。 第一端可操作地固定到发动机静态结构。 第二端被配置为相对于整流罩密封。 密封板包括在第一和第二端之间的基本上在轴向方向上延伸的部分，并且构造成允许第二端响应于热增长而相对于第一端沿轴向方向远离整流罩移动。

公开(公告)号：WO2014171994A3

公开(公告)日：2014-10-23

申请号：PCT/US2014/014116

申请日：2014-01-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： PORTER, Steven D. ,  FEINDEL, David T. ,  BUDNICK, Matthew ,  CHUONG, Conway

IPC: F01D25/00 ,  F01D21/00 ,  F01D11/00

Abstract: A borescope plug assembly includes a borescope plug having a shaft section and a tip section, a bushing engageable with the shaft section and a seal engageable with the tip section.

Abstract translation: 管道镜插头组件包括具有轴部和尖端部的管道镜插头，可与轴部接合的套管和可与尖端部接合的密封件。

公开(公告)号：WO2014143317A2

公开(公告)日：2014-09-18

申请号：PCT/US2013/076758

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BUDNICK, Matthew ,  CHUONG, Conway ,  SCOTT, Jonathan A.

CPC classification number: F01D11/005 ,  F01D25/162 ,  F01D25/246

Abstract: A turbine seal system comprises an annular structural frame, a circumferential ring, a fairing and a seal. The circumferential ring is joined to the annular structural frame. The fairing is disposed within the annular structural frame and is engaged with the circumferential ring to limit circumferential rotation of the fairing with respect to the annular structural frame. The seal extends between the fairing and the circumferential ring. In one embodiment, the structural component comprises a ring-strut-ring turbine exhaust case.

Abstract translation: 涡轮密封系统包括环形结构框架，圆周环，整流罩和密封件。 周向环连接到环形结构框架。 整流罩设置在环形结构框架内并与周向环接合以限制整流罩相对于环形结构框架的周向旋转。 密封件在整流罩和周向环之间延伸。 在一个实施例中，结构部件包括环形支撑环式涡轮机排气箱。