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公开(公告)号：US20160169034A1
公开(公告)日：2016-06-16
申请号：US14969774
申请日：2015-12-15
Applicant: United Technologies Corporation
Inventor： Steven Clarkson , Daniel K. Van Ness, II , Paul Thomas Rembish
CPC classification number: F01D25/02 , B64D15/12 , B64D27/10 , B64D29/00 , F01D17/105 , F01D21/10 , F01D25/10 , F01D25/24 , F02C7/047 , F02C7/05 , F04D27/0215 , F04D27/023 , F04D29/545 , F04D29/584 , F05D2220/323 , F05D2220/36 , F05D2260/20 , F05D2270/096
Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.
Abstract translation: 燃气涡轮发动机的壳体包括芯体。 芯体限定了纵向延伸的芯流动路径，连接与外部环境流体连通的芯流动路径的横向延伸的放气管道，以及横跨排气管道的结构支撑构件。 加热元件连接到芯体并且与结构支撑构件热连通。
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2.发明申请公开(公告)号：US20150226116A1
公开(公告)日：2015-08-13
申请号：US14429071
申请日：2013-09-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel W. Major , Gregory E. Reinhardt , Paul Thomas Rembish , Barry William Spaulding , Donald Summers
CPC classification number: F02C3/073 , F01D17/162 , F01D25/243 , F02C7/20 , F02C7/36 , F05D2220/36 , F05D2230/60 , F05D2230/70 , F05D2260/31 , F05D2260/40311 , F05D2260/79 , Y10T29/49233
Abstract: A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.
Abstract translation: 用于将风扇驱动齿轮系统模块固定在燃气涡轮发动机内的连接组件包括通过径向延伸的紧固件可拆卸地彼此固定的第一和第二构件。
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公开(公告)号：US10767555B2
公开(公告)日：2020-09-08
申请号：US15877077
申请日：2018-01-22
Applicant: United Technologies Corporation
Inventor： Daniel W. Major , Gregory E. Reinhardt , Paul Thomas Rembish , Barry William Spaulding , Donald Summers
Abstract: A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.
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公开(公告)号：US20180142620A1
公开(公告)日：2018-05-24
申请号：US15877077
申请日：2018-01-22
Applicant: United Technologies Corporation
Inventor： Daniel W. Major , Gregory E. Reinhardt , Paul Thomas Rembish , Barry William Spaulding , Donald Summers
Abstract: A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.
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Patent Agency Ranking
公开(公告)号：US09896964B2
公开(公告)日：2018-02-20
申请号：US14969774
申请日：2015-12-15
Applicant: United Technologies Corporation
Inventor： Steven Clarkson , Daniel K. Van Ness, II , Paul Thomas Rembish
IPC: F01D25/02 , F01D25/24 , F01D25/10 , F01D21/10 , F01D17/10 , B64D27/10 , B64D15/12 , B64D29/00 , F02C7/047 , F02C7/05 , F04D29/54 , F04D29/58 , F04D27/02
CPC classification number: F01D25/02 , B64D15/12 , B64D27/10 , B64D29/00 , F01D17/105 , F01D21/10 , F01D25/10 , F01D25/24 , F02C7/047 , F02C7/05 , F04D27/0215 , F04D27/023 , F04D29/545 , F04D29/584 , F05D2220/323 , F05D2220/36 , F05D2260/20 , F05D2270/096
Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.
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公开(公告)号：US10167737B2
公开(公告)日：2019-01-01
申请号：US14433861
申请日：2013-03-12
Applicant: United Technologies Corporation
Inventor： Gregory E. Reinhardt , Paul Thomas Rembish , Steven L. Conner , Thomas B. Hyatt , Steven J. Feigleson , Carl Brian Klinetob
Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.
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公开(公告)号：US09964032B2
公开(公告)日：2018-05-08
申请号：US14429071
申请日：2013-09-12
Applicant: United Technologies Corporation
Inventor： Daniel W. Major , Gregory E. Reinhardt , Paul Thomas Rembish , Barry William Spaulding , Donald Summers
CPC classification number: F02C3/073 , F01D17/162 , F01D25/243 , F02C7/20 , F02C7/36 , F05D2220/36 , F05D2230/60 , F05D2230/70 , F05D2260/31 , F05D2260/40311 , F05D2260/79 , Y10T29/49233
Abstract: A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.
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公开(公告)号：US20160169036A1
公开(公告)日：2016-06-16
申请号：US14969719
申请日：2015-12-15
Applicant: United Technologies Corporation
Inventor： Steven Clarkson , Daniel K. Van Ness, II , Paul Thomas Rembish
CPC classification number: F01D25/10 , F01D17/105 , F01D25/02 , F01D25/18 , F01D25/24 , F02C7/047 , F02C9/18 , F04D27/0215 , F04D29/522 , F04D29/584 , F04D29/5853 , F05D2220/32 , F05D2260/20 , F05D2260/4031 , Y02T50/675
Abstract: A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.
Abstract translation: 用于燃气涡轮发动机的壳体包括限定轴向延伸的芯流动路径的壳体，连接与外部环境流体连通的芯流动路径的径向延伸的排气管道，以及横跨排气管道的结构支撑构件。 润滑剂管道连接到壳体并且与结构支撑构件热连通。
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公开(公告)号：US20150275694A1
公开(公告)日：2015-10-01
申请号：US14433861
申请日：2013-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gregory E. Reinhardt , Paul Thomas Rembish , Steven L. Conner , Thomas B. Hyatt , Steven J. Feigleson , Carl Brian Klinetob
CPC classification number: F01D25/26 , F01D9/02 , F01D25/162 , F05D2220/36 , F05D2230/64 , F05D2230/642 , F05D2230/644 , F05D2260/311 , F05D2260/36 , F05D2260/39 , Y10T29/49323
Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.
Abstract translation: 涡轮风扇发动机结构导叶安装在内端的核心发动机外壳结构的前隔板和外端的风扇外壳上。 多个剪切销从结构导向叶片的后部延伸到限定在隔板中的相应的多个开口以用于承受圆周载荷。
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