-
公开(公告)号：US20160363131A1
公开(公告)日：2016-12-15
申请号：US14623356
申请日：2015-02-16
Applicant: United Technologies Corporation
Inventor： John C. Ditomasso , Gregory E. Reinhardt
CPC classification number: F04D29/542 , F01D25/162 , F01D25/243 , F01D25/28 , F02C7/20 , F04D29/644 , F05D2250/11
Abstract: A center body support for a gas turbine engine includes an outer annular wall. An aft flange extends radially outward from the outer annular wall. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange, brace and forward portion of the outer annual wall provide a unitary, one-piece structure.
Abstract translation: 用于燃气涡轮发动机的中心体支撑件包括外环形壁。 后凸缘从外环形壁径向向外延伸。 支架将后翼缘连接到外环形壁的前部。 外墙法兰，支架和外墙的前部提供了一体的单件式结构。
-
公开(公告)号：US20150252679A1
公开(公告)日：2015-09-10
申请号：US14427323
申请日：2013-03-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew Pope , David J. Yudichak , John P. Lucashu , Gregory E. Reinhardt , John C. Ditomasso , Steven L. Conner , Carl Brian Klinetob , Jason Leroux
CPC classification number: F01D9/02 , F01D1/02 , F01D5/147 , F01D9/041 , F05D2230/23 , F05D2240/12 , Y02T50/671
Abstract: A static guide vane for use in a fan section of a gas turbine engine includes an outer platform and an inner platform. The inner and outer platforms are connected by an airfoil. The airfoil have channels extending into a main body of the airfoil to reduce the weight of the vane. A cover closes off the channels with the cover providing a portion of the airfoil.
Abstract translation: 用于燃气涡轮发动机的风扇部分的静态导向叶片包括外平台和内平台。 内外平台通过翼型连接。 翼型件具有延伸到翼型件的主体中的通道，以减小叶片的重量。 盖子封闭通道，盖子提供翼型的一部分。
-
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.
-
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.
-
公开(公告)号：US20160208697A1
公开(公告)日：2016-07-21
申请号：US15084970
申请日：2016-03-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Marc J. Muldoon , Gregory E. Reinhardt
CPC classification number: F02C7/06 , F01D11/005 , F01D11/02 , F01D11/04 , F01D25/16 , F01D25/183 , F01D25/20 , F01D25/28 , F02C3/10 , F02C6/08 , F02C7/20 , F02C7/28 , F02K3/06 , F05D2220/36 , F05D2240/56 , F05D2260/98 , F05D2300/224 , F16J15/40
Abstract: A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame. The bearing compartment is arranged within the air compartment and includes first and second contact seals arranged on either side of the bearing. The air compartment includes multiple air seals. A high pressure compressor is fluidly connected to the air compartment and is configured to provide high pressure air to the air compartment. A method of providing pressurized air to a buffer system includes sealing a bearing compartment with contact seals, surrounding the bearing compartment with an air compartment, and supplying high pressure air to the air compartment.
Abstract translation: 用于燃气涡轮发动机的中涡轮机框架缓冲系统包括通过轴承支撑轴的中涡轮机框架。 空气隔间和轴承室设置在中间涡轮机框架的径向内侧。 轴承室设置在空气室内，并且包括布置在轴承两侧的第一和第二接触密封件。 空气室包括多个空气密封。 高压压缩机流体地连接到空气室，并且构造成向空气室提供高压空气。 向缓冲系统提供加压空气的方法包括用接触密封件密封轴承室，用空气室包围轴承室，并向空气室供应高压空气。
-
Patent Agency Ranking
公开(公告)号：US09382844B2
公开(公告)日：2016-07-05
申请号：US13879471
申请日：2013-01-07
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon , Gregory E. Reinhardt
IPC: F02C7/28 , F02C7/20 , F01D11/02 , F01D25/16 , F01D25/28 , F16J15/40 , F01D11/04 , F01D25/18 , F01D25/20 , F02K3/06 , F02C6/08
CPC classification number: F02C7/06 , F01D11/005 , F01D11/02 , F01D11/04 , F01D25/16 , F01D25/183 , F01D25/20 , F01D25/28 , F02C3/10 , F02C6/08 , F02C7/20 , F02C7/28 , F02K3/06 , F05D2220/36 , F05D2240/56 , F05D2260/98 , F05D2300/224 , F16J15/40
Abstract: A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame. The bearing compartment is arranged within the air compartment and includes first and second contact seals arranged on either side of the bearing. The air compartment includes multiple air seals. A high pressure compressor is fluidly connected to the air compartment and is configured to provide high pressure air to the air compartment. A method of providing pressurized air to a buffer system includes sealing a bearing compartment with contact seals, surrounding the bearing compartment with an air compartment, and supplying high pressure air to the air compartment.
-
公开(公告)号：US20140075951A1
公开(公告)日：2014-03-20
申请号：US13879471
申请日：2013-01-07
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon , Gregory E. Reinhardt
IPC: F02C7/20
CPC classification number: F02C7/06 , F01D11/005 , F01D11/02 , F01D11/04 , F01D25/16 , F01D25/183 , F01D25/20 , F01D25/28 , F02C3/10 , F02C6/08 , F02C7/20 , F02C7/28 , F02K3/06 , F05D2220/36 , F05D2240/56 , F05D2260/98 , F05D2300/224 , F16J15/40
Abstract: A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame. The bearing compartment is arranged within the air compartment and includes first and second contact seals arranged on either side of the bearing. The air compartment includes multiple air seals. A high pressure compressor is fluidly connected to the air compartment and is configured to provide high pressure air to the air compartment. A method of providing pressurized air to a buffer system includes sealing a bearing compartment with contact seals, surrounding the bearing compartment with an air compartment, and supplying high pressure air to the air compartment.
Abstract translation: 用于燃气涡轮发动机的中涡轮机框架缓冲系统包括通过轴承支撑轴的中涡轮机框架。 空气隔间和轴承室设置在中间涡轮机框架的径向内侧。 轴承室设置在空气室内，并且包括布置在轴承两侧的第一和第二接触密封件。 空气室包括多个空气密封。 高压压缩机流体地连接到空气室，并且构造成向空气室提供高压空气。 向缓冲系统提供加压空气的方法包括用接触密封件密封轴承室，用空气室包围轴承室，并向空气室供应高压空气。
-
公开(公告)号：US11433322B2
公开(公告)日：2022-09-06
申请号：US16550020
申请日：2019-08-23
Applicant: United Technologies Corporation
Inventor： Daniel L. Gysling , Gregory E. Reinhardt , Daniel A. Szkrybalo
Abstract: A machine has a first member; a second member; a third member; a bearing having an inner race mounted to the second member and an outer race mounted to the third member; a damper chamber between the first member and the third member; a fluid outlet in the first member to the damper chamber; a fluid supply flowpath to the fluid outlet; and an unvented chamber open to and locally above the fluid supply flowpath.
-
公开(公告)号：US10927709B2
公开(公告)日：2021-02-23
申请号：US16000223
申请日：2018-06-05
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon , Gregory E. Reinhardt
Abstract: A gas turbine includes a shaft, a turbine coupled with the shaft for rotation with the shaft, and a bearing coupled with the shaft to facilitate rotation of the shaft. A bearing nut is adjacent the bearing on the shaft. The turbine has a first load path and the bearing has a second load path. The bearing nut exerts a force on the bearing such that the first load path is not aligned with the second load path relative to a central axis of the gas turbine engine. A method of assembling a gas turbine engine is also disclosed.
-
公开(公告)号：US20200025030A1
公开(公告)日：2020-01-23
申请号：US16286970
申请日：2019-02-27
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Todd A. Davis , Gregory E. Reinhardt , Enzo DiBenedetto
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
-
-
-
-
-
-
-
-
-
Search Results
40
records
(took 0.014 seconds)
