公开(公告)号：US20180080373A1

公开(公告)日：2018-03-22

申请号：US15268713

申请日：2016-09-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Tania Bhatia Kashyap ,  Mark F. Zelesky ,  Arthur W. Utay ,  Gabriel L. Suciu ,  Thomas N. Slavens ,  Kevin L. Rugg ,  Brian Merry

IPC: F02C3/107 ,  F02C3/14

CPC classification number: F02C3/107 ,  F02C3/145 ,  F02C7/04 ,  F05D2240/40 ,  F05D2250/30

Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

公开(公告)号：US09909506B2

公开(公告)日：2018-03-06

申请号：US14759979

申请日：2013-01-28

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis

IPC: F02C9/18 ,  F02K3/10 ,  F02K3/077 ,  F01D1/04 ,  F02K1/78 ,  F02K3/075 ,  F02C3/04 ,  F02C3/14 ,  F02C7/08 ,  F02K3/02

CPC classification number: F02C9/18 ,  F01D1/04 ,  F02C3/04 ,  F02C3/145 ,  F02C7/08 ,  F02K1/78 ,  F02K3/025 ,  F02K3/075 ,  F02K3/077 ,  F02K3/10 ,  F05D2220/32 ,  F05D2250/31

Abstract: A gas turbine engine has a fan rotor for delivering air axially downstream into a core engine duct, which sequentially passes a turbine, a combustor, and a compressor. The core engine duct extends to a turning supply duct configured to turn the core air flow axially upstream so that the core air sequentially passes through the compressor, combustor and turbine, and into an exhaust conduit which turns the core airflow radially outwardly and axially downstream into an exhaust duct. A door is selectively opened to communicate a portion of the core airflow in the core engine duct to an augmentor with the exhaust duct isolated from the augmentor. The door is at a location prior to the core airflow reaching the compressor. A method is also disclosed.

公开(公告)号：US09835052B2

公开(公告)日：2017-12-05

申请号：US15478671

申请日：2017-04-04

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F02C7/36 ,  F01D25/16 ,  F04D29/32 ,  F04D25/04 ,  F04D19/02 ,  F01D5/06 ,  F01D9/04 ,  F02C3/107 ,  F01D15/12 ,  F02C3/04 ,  F02K3/06

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/041 ,  F01D15/12 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/028 ,  F04D25/045 ,  F04D29/056 ,  F04D29/325 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US20170298767A1

公开(公告)日：2017-10-19

申请号：US15478706

申请日：2017-04-04

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F01D25/16 ,  F01D9/04 ,  F04D19/02 ,  F01D5/06 ,  F04D29/32 ,  F04D27/00 ,  F04D25/04 ,  F04D25/02 ,  F02C3/04 ,  F02K3/06

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/041 ,  F01D15/12 ,  F01D25/162 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/028 ,  F04D25/045 ,  F04D27/009 ,  F04D29/056 ,  F04D29/325 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US20170276010A1

公开(公告)日：2017-09-28

申请号：US15606522

申请日：2017-05-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F02K3/06 ,  F04D25/04 ,  F04D19/00 ,  F01D5/06 ,  F04D29/053

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades supported by a fan shaft support defining a fan shaft support lateral and transverse stiffness. A gear system connected to the fan shaft including a ring gear defining a ring gear lateral and transverse stiffness, a gear mesh defining a gear mesh lateral and transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral and transverse stiffness is less than 12% of a respective one of the gear mesh lateral and transverse stiffness. A flexible support supports the gear system and defines a flexible support lateral and transverse stiffness. At least one of the flexible support lateral and transverse stiffness is less than 11% of a respective one of the fan shaft support lateral and transverse stiffness.

公开(公告)号：US20170234159A1

公开(公告)日：2017-08-17

申请号：US15478671

申请日：2017-04-04

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F01D25/16 ,  F04D25/04 ,  F02C7/36 ,  F01D5/06 ,  F01D9/04 ,  F04D29/32 ,  F04D19/02

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/041 ,  F01D15/12 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/028 ,  F04D25/045 ,  F04D29/056 ,  F04D29/325 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US20170175632A1

公开(公告)日：2017-06-22

申请号：US14974779

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis

IPC: F02C7/18 ,  F02K3/06 ,  F02C3/10

CPC classification number: F02C7/185 ,  F01D25/162 ,  F02C3/10 ,  F02C6/08 ,  F02C7/12 ,  F02C7/125 ,  F02C7/141 ,  F02C7/18 ,  F02K3/06 ,  F05D2240/129 ,  F05D2250/51 ,  F05D2260/213 ,  Y02T50/676

Abstract: A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine.

公开(公告)号：US20160376998A1

公开(公告)日：2016-12-29

申请号：US14207970

申请日：2014-03-13

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis

IPC: F02C9/22 ,  F02C9/18 ,  F02K3/06 ,  F02C3/06

CPC classification number: F02C9/22 ,  F02C3/10 ,  F02C9/20 ,  F02K3/06 ,  F02K3/077

Abstract: A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compressor and a first turbine section in fluid communication with the combustor. The first turbine section includes a low pressure turbine that drives the first fan section. A second fan section is supported between the first fan section and the compressor and is driven by a second turbine section disposed between the second fan section and the compressor for driving the second fan section.

Abstract translation: 所公开的燃气涡轮发动机包括：第一风扇部分，其包括可围绕轴线旋转的多个风扇叶片;与第一风扇部分流体连通的压缩机;与压缩机流体连通的燃烧器;以及与该压缩机流体连通的第一涡轮机部分 燃烧器。 第一涡轮机部分包括驱动第一风扇部分的低压涡轮机。 第二风扇部分支撑在第一风扇部分和压缩机之间，并且由布置在第二风扇部分和压缩机之间的第二涡轮部分驱动，用于驱动第二风扇部分。

公开(公告)号：US20160312740A1

公开(公告)日：2016-10-27

申请号：US14519272

申请日：2014-10-21

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Walter A. Ledwith, JR. ,  Christopher J. Hanlon

IPC: F02K3/075 ,  F02K3/077 ,  F02C3/10

CPC classification number: F02K3/075 ,  F02C3/10 ,  F02K3/077

Abstract: A gas turbine engine includes an auxiliary airflow control system to provide selective communication of a portion of a second stream from a second stream flow path into a third stream flow path, the auxiliary airflow control system in communication with a high temperature flow sourced from the turbine section.

Abstract translation: 燃气涡轮发动机包括辅助气流控制系统，以提供将第二流的一部分从第二流动路径选择性地连通到第三流动流动路径中，所述辅助气流控制系统与来自涡轮机的高温流体相通 部分。

公开(公告)号：US20160169102A1

公开(公告)日：2016-06-16

申请号：US14948991

申请日：2015-11-23

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis

IPC: F02C3/14 ,  F02C3/107 ,  F02C7/12 ,  F02C3/06

CPC classification number: F02C3/145 ,  F02C3/06 ,  F02C3/107 ,  F02C7/12 ,  F02C7/143 ,  F02C7/36 ,  F02K3/06 ,  F02K3/115 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2260/211 ,  F05D2260/40311 ,  Y02T50/675

Abstract: A reverse flow gas turbine engine includes a propulsor section which includes a propulsor compressor section and a propulsor turbine section. The propulsor section includes a fan section and a geared architecture. The fan section is driven by the propulsor turbine section. A core section is arranged fluidly between the propulsor compressor section and the propulsor turbine section. The core section includes a reverse flow duct that reverses a core flow through the core section. At least one of the propulsor section and the core section has a two-spool arrangement.

Abstract translation: 逆流燃气涡轮发动机包括具有推进压缩机部分和推进涡轮部分的推进部分。 推进器部分包括风扇部分和齿轮架构。 风扇部分由推进涡轮机部分驱动。 在推进压缩机部分和推进涡轮机部分之间流体地设置有核心部分。 核心部分包括反向流动管道，其反转通过芯部分的芯流。 推进器段和芯部中的至少一个具有双线轴布置。