公开(公告)号：US11286852B2

公开(公告)日：2022-03-29

申请号：US16568525

申请日：2019-09-12

Applicant: United Technologies Corporation

Inventor： William K. Ackermann ,  Peter M. Munsell

IPC: F02C6/08 ,  F01D25/12 ,  F02C7/18 ,  F01D11/04 ,  F01D25/16 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18

Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.

公开(公告)号：US11098644B2

公开(公告)日：2021-08-24

申请号：US16677721

申请日：2019-11-08

Applicant: United Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F02C6/08 ,  F01D11/06 ,  F01D25/12 ,  F01D11/04 ,  F02C9/18 ,  F02C7/28 ,  F02C7/06

Abstract: A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.

公开(公告)号：US20180216483A1

公开(公告)日：2018-08-02

申请号：US15939508

申请日：2018-03-29

Applicant: United Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F01D9/06 ,  F01D25/24 ,  F01D25/16 ,  F01D5/06 ,  F02C6/08 ,  F01D25/08 ,  F04D29/32 ,  F02C7/36

Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and the front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.

公开(公告)号：US20180216482A1

公开(公告)日：2018-08-02

申请号：US15939467

申请日：2018-03-29

Applicant: United Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F01D9/06 ,  F01D25/24 ,  F01D25/16 ,  F01D5/06 ,  F02C6/08 ,  F01D25/08 ,  F04D29/32 ,  F02C7/36

Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.

公开(公告)号：US20160032775A1

公开(公告)日：2016-02-04

申请号：US14773876

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Cheng-Zhang Wang ,  Jorn A. Glahn ,  David F. Cloud ,  Peter M. Munsell ,  Clifton J. Crawley, JR. ,  Robert Newman ,  Michelle Diana Stearns

IPC: F01D25/24

CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D9/065 ,  F01D25/162 ,  F02C7/18 ,  F05D2240/14 ,  F05D2260/14 ,  F05D2260/20 ,  F05D2260/2212 ,  F05D2260/97 ,  Y02T50/676

Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

Abstract translation: 涡轮发动机包括具有低压涡轮机的涡轮机部分和围绕轴线布置的涡轮机壳体。 框架组件限定外腔和内腔，其中外腔包括构造并适于将冷却空气与涡轮机壳连通的至少一个开口。 传送管设置在外腔内并且被配置和适于接收冷却空气。 传送管包括弯曲部，该弯曲部被配置为向外腔内的冷却空气赋予圆周速度。

公开(公告)号：US10731563B2

公开(公告)日：2020-08-04

申请号：US15882058

申请日：2018-01-29

Applicant: United Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F02C1/00 ,  F02C7/18 ,  F01D25/18 ,  F01D25/22 ,  F02C6/08

Abstract: A method of designing a buffer system for a gas turbine engine according to an example of the present disclosure includes, among other things, configuring a heat exchanger to define a first inlet and a first outlet fluidly coupled to each other and a second inlet and a second outlet fluidly coupled to each other, configuring the first inlet to receive air from first and second air sources that are selectively fluidly coupled to the first inlet, configuring the second inlet to receive air from a third air source fluidly that is coupled to the second inlet, and configuring the first outlet to provide cooled pressurized air to multiple fluid-supplied areas that are located remotely from one another and that are fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment of a gas turbine engine.

公开(公告)号：US20200173302A1

公开(公告)日：2020-06-04

申请号：US16779768

申请日：2020-02-03

Applicant: United Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F04D29/32 ,  F01D25/08 ,  F02C7/36 ,  F02C6/08 ,  F01D9/06 ,  F01D25/24 ,  F01D25/16 ,  F01D5/06

Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure is mounted to the front center body case structure to rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.

公开(公告)号：US20180149035A1

公开(公告)日：2018-05-31

申请号：US15865393

申请日：2018-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F02C7/36 ,  F01D9/06 ,  F01D25/08 ,  F01D25/16 ,  F04D29/32 ,  F01D5/06 ,  F02C6/08 ,  F01D25/24

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/16 ,  F01D25/24 ,  F02C6/08 ,  F02C7/36 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/55 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a low pressure compressor, and a high pressure compressor axially aft of the low pressure compressor. A first case structure defines a core flow path for core airflow into the low pressure compressor and has a forward end and an aft end. A second case structure defines a core flow path for core airflow into the high pressure compressor and is mounted to the aft end of the first case structure. A geared architecture is at least partially supported by the first case structure. A first bearing structure is mounted to the first case structure to rotationally support a fan shaft that connects with the geared architecture to drive the fan. A flex support provides a flexible attachment of the geared architecture within the first case structure. A fan drive turbine drives the geared architecture to drive the fan at a speed lower than a speed of the fan drive turbine.

公开(公告)号：US09410483B2

公开(公告)日：2016-08-09

申请号：US14640251

申请日：2015-03-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F02C7/06 ,  F02C7/12 ,  F02C7/28 ,  F01D25/16 ,  F02K3/06 ,  F02C7/36

CPC classification number: F02C7/06 ,  F01D25/16 ,  F02C7/12 ,  F02C7/28 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.

公开(公告)号：US20200263604A1

公开(公告)日：2020-08-20

申请号：US16677721

申请日：2019-11-08

Applicant: United Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F02C6/08 ,  F01D11/06 ,  F01D25/12 ,  F01D11/04 ,  F02C9/18

Abstract: A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.