公开(公告)号：US20200208538A1

公开(公告)日：2020-07-02

申请号：US16453358

申请日：2019-06-26

Applicant: United Technologies Corporation

Inventor： Jorge I. Farah ,  Steven D. Porter ,  Paul K. Sanchez ,  Joseph J. Sedor

IPC: F01D25/28 ,  F02C7/20 ,  F01D25/16 ,  F01D9/06

Abstract: A method of assembling a mid-turbine frame includes engaging at least two tabs in a radially inner end of at least one spoke in a groove in an inner frame case. The at least one spoke is secured to the inner frame case with a central bolt extending through the inner frame case into the at least one spoke.

公开(公告)号：US20160069200A1

公开(公告)日：2016-03-10

申请号：US14787332

申请日：2014-05-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Richard N. Allen ,  Steven D. Porter ,  Paul K. Sanchez ,  Sandra S. Pinero

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/042 ,  F01D5/14 ,  F01D5/141 ,  F01D9/02 ,  F01D9/04 ,  F01D9/047 ,  F01D25/24 ,  F05D2230/53 ,  Y02T50/671 ,  Y02T50/673

Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract translation: 叶片具有在径向外平台和径向内平台之间延伸的翼型件。 至少一个平台具有标称径向较薄的部分，以及限定径向较厚部分的垫。 垫的径向厚度大于标称径向较薄部分的厚度。 垫片围绕在径向外平台的一侧的翼型件的外周边。 垫具有变化的径向厚度。 还公开了中涡轮机架和燃气涡轮发动机。

公开(公告)号：US20160032778A1

公开(公告)日：2016-02-04

申请号：US14776719

申请日：2014-02-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul K. Sanchez

IPC: F01D25/24 ,  F01D5/02 ,  F01D9/04 ,  F02C3/04

CPC classification number: F01D25/246 ,  B64D29/08 ,  F01D5/02 ,  F01D9/041 ,  F02C3/04 ,  F02C7/20 ,  F05D2220/30 ,  F05D2240/35

Abstract: A turbine engine includes a full ring fairing having at least a first and second keyed feature. The full ring fairing is rotatable so that the second keyed feature is in the first keyed feature position relative to the turbine engine.

Abstract translation: 涡轮发动机包括具有至少第一和第二键控特征的全环整流罩。 整圈整流罩可旋转，使得第二键合特征相对于涡轮发动机处于第一键控特征位置。

公开(公告)号：US10371010B2

公开(公告)日：2019-08-06

申请号：US14598574

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Jorge I. Farah ,  Steven D. Porter ,  Paul K. Sanchez ,  Joseph J. Sedor

IPC: F01D25/28 ,  F01D9/06 ,  F01D25/16 ,  F02C7/20

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a bolt opening and at least one spoke for connecting an outer frame case to the inner frame case that includes an inlet passage that extends in a radial direction. A central bolt extends through the bolt opening for securing at least one spoke to the inner frame case.

公开(公告)号：US09512738B2

公开(公告)日：2016-12-06

申请号：US13753821

申请日：2013-01-30

Applicant: United Technologies Corporation

Inventor： Paul K. Sanchez ,  Kalpendu J. Parekh ,  William A. Daniels ,  John S. Tu

IPC: F01D5/18 ,  F01D25/14 ,  F01D25/12 ,  F01D25/24 ,  F01D25/16

CPC classification number: F02C7/20 ,  F01D25/12 ,  F01D25/14 ,  F01D25/16 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F02C7/12 ,  F02K3/04 ,  F05D2220/36 ,  F05D2260/20

Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.

Abstract translation: 涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器部分，与燃烧器流体连通的高压涡轮机，与高压涡轮机流体连通的低压涡轮机，以及位于轴向 在高压涡轮机和低压涡轮机之间。 中间涡轮机框架包括外框架壳体，内框架壳体和多个中空轮辐，其将负载从内框架壳体分配到外框架壳体。 轮辐是中空的，以允许冷却气流通过轮辐供应到内框架壳体。

公开(公告)号：US20160208655A1

公开(公告)日：2016-07-21

申请号：US14598574

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Jorge I. Farah ,  Steven D. Porter ,  Paul K. Sanchez ,  Joseph J. Sedor

IPC: F01D25/28

CPC classification number: F01D25/28 ,  F01D9/065 ,  F01D25/162 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/31

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a bolt opening and at least one spoke for connecting an outer frame case to the inner frame case that includes an inlet passage that extends in a radial direction. A central bolt extends through the bolt opening for securing at least one spoke to the inner frame case.

Abstract translation: 用于燃气涡轮发动机的中涡轮机框架包括内框架壳体，其包括螺栓开口和用于将外框架壳体连接到内框架的至少一个辐条，所述内框架壳体包括沿径向方向延伸的入口通道。 中心螺栓延伸穿过螺栓开口，用于将至少一个辐条固定到内框架壳体上。

公开(公告)号：US20160153296A1

公开(公告)日：2016-06-02

申请号：US14900737

申请日：2014-06-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Richard N Allen ,  Paul K. Sanchez ,  Steven D. Porter ,  Jonathan Lemoine

IPC: F01D9/04 ,  F01D11/02

CPC classification number: F01D9/041 ,  F01D5/082 ,  F01D11/003 ,  F01D11/02 ,  F05D2240/12 ,  F05D2240/80

Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.

Abstract translation: 燃气涡轮发动机内的界面包括由叶片平台的一部分限定的密封表面。 密封件与所述密封表面接触。 屏障横向于密封表面。

公开(公告)号：US10961870B2

公开(公告)日：2021-03-30

申请号：US16426707

申请日：2019-05-30

Applicant: United Technologies Corporation

Inventor： Joshua Daniel Winn ,  Alexander Broulidakis ,  Paul K. Sanchez ,  Anthony P Cherolis ,  Joseph J. Sedor ,  Christopher Treat

IPC: F01D25/28 ,  F01D5/02 ,  F01D25/26 ,  F01D25/12 ,  F01D9/06 ,  F01D25/16 ,  F02C7/12

Abstract: A method of cooling a portion of a gas turbine engine includes positioning a tie rod relative to an inner frame case. The tie rod includes a bushing opening and the inner frame case includes a fastener opening. A fastener is secured through the fastener opening in the inner frame case to a threaded bushing located in the bushing opening. The threaded bushing includes a distal end that forms a clearance gap with the inner frame case. Heat is transferred from the fastener through the threaded bushing to prevent the fastener from creeping.

公开(公告)号：US10941669B2

公开(公告)日：2021-03-09

申请号：US16228994

申请日：2018-12-21

Applicant: United Technologies Corporation

Inventor： Matthew A. Hough ,  Russell B. Hanson ,  John S. Tu ,  Paul F. Croteau ,  Paul K. Sanchez ,  Stephen C. Harmon ,  Joshua C. Rathgeb

IPC: F01D9/06 ,  F01D9/02 ,  F01D25/24

Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

公开(公告)号：US10107120B2

公开(公告)日：2018-10-23

申请号：US15245798

申请日：2016-08-24

Applicant: United Technologies Corporation

Inventor： Paul K. Sanchez ,  John S. Tu ,  Kalpendu J. Parekh ,  William A. Daniels

IPC: F01D25/24 ,  F01D9/06 ,  F01D25/28 ,  F02C7/12 ,  F01D25/16 ,  F01D25/12 ,  F02C3/04 ,  F02C6/08

Abstract: A mid-turbine frame (MTF) for a gas turbine engine includes an inner manifold directing air to a turbine rotor of the gas turbine engine. The MTF includes an outer MTF case and an inner MTF case. The inner manifold of the MTF is located in the inner case of the MTF.