公开(公告)号：US10047676B2

公开(公告)日：2018-08-14

申请号：US15137561

申请日：2016-04-25

Applicant: United Technologies Corporation

Inventor： Joseph Stack ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Kurt J. Sobanski

IPC: F02C1/00 ,  F02C7/24 ,  F02C3/04 ,  F02C7/20 ,  F02C7/25

Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall. An electronic module assembly of the electromechanical component is connected to the mechanical component and includes a housing, a mounting frame located in the housing and an electronic module secured to the mounting frame. The electronic module is operably connected to the mechanical component via a module cable. A vibration isolator is located in the housing to locate and support the mounting frame therein. The vibration isolator is configured to vibrationally isolate the electronic module from gas turbine engine vibrations. A cover plate is secured to the housing and the first side of the firewall, while the housing extends from the cover plate through a module opening in the firewall to a second side of the firewall having a lower operating temperature than the first side.

公开(公告)号：US20180223693A1

公开(公告)日：2018-08-09

申请号：US15424930

申请日：2017-02-06

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Ioannis Alvanos

IPC: F01D25/30 ,  F02K1/04 ,  F02K3/06

CPC classification number: F01D25/30 ,  F01D9/02 ,  F02C3/04 ,  F02K1/04 ,  F02K1/48 ,  F02K3/06 ,  F05D2240/14 ,  F05D2260/96 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.

公开(公告)号：US10036329B2

公开(公告)日：2018-07-31

申请号：US14430315

申请日：2013-03-12

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu

IPC: F02C9/18 ,  F02C7/14 ,  F02K3/115 ,  F02C6/08 ,  F02C3/107 ,  F02C7/18 ,  F01D17/10 ,  F02K3/04 ,  F02K3/075

CPC classification number: F02C9/18 ,  F01D17/105 ,  F02C3/107 ,  F02C6/08 ,  F02C7/14 ,  F02C7/18 ,  F02K3/04 ,  F02K3/075 ,  F02K3/115 ,  F05D2260/213 ,  F05D2270/3062 ,  Y02T50/676

Abstract: A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a duct. The heat exchanger is configured to receive bypass flow from the bypass flow path. The duct is in fluid communication with the compressor section and is configured to pass bleed air through the heat exchanger.

公开(公告)号：US20180202369A1

公开(公告)日：2018-07-19

申请号：US15921934

申请日：2018-03-15

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  F05D2260/40311

Abstract: A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. A bypass ratio is defined as a volume of air delivered as bypass flow compared to a volume of air delivered into the core housing. The overall pressure ratio is greater than or equal to about 45.0, and the bypass ratio is greater than or equal to about 11.0.

公开(公告)号：US10024235B2

公开(公告)日：2018-07-17

申请号：US14608227

申请日：2015-01-29

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  James D. Hill ,  Jesse M. Chandler

IPC: F02C3/14 ,  F02C3/06 ,  F02C3/10 ,  F02C6/02 ,  F02C7/05 ,  F02K3/12

Abstract: A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.

公开(公告)号：US20180187605A1

公开(公告)日：2018-07-05

申请号：US15908475

申请日：2018-02-28

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Brian D. Merry ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F01D25/16 ,  F01D21/04 ,  F02K3/075 ,  F02K3/02 ,  F02C3/06 ,  F01D21/02

CPC classification number: F02C7/36 ,  F01D21/02 ,  F01D21/04 ,  F01D25/16 ,  F02C3/06 ,  F02C3/107 ,  F02K3/025 ,  F02K3/075 ,  F05D2270/091 ,  Y02T50/671

Abstract: A turbofan engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a shaft configured to be driven by the turbine section and coupled to the compressor section through a first torque load path, and a speed reduction mechanism configured to be driven by the shaft through a second torque load path separate from the first load path for rotating the fan.

公开(公告)号：US20180187602A1

公开(公告)日：2018-07-05

申请号：US15907942

申请日：2018-02-28

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian Merry ,  Jesse M. Chandler ,  Frederick M. Schwarz

IPC: F02C7/143 ,  F02C6/08 ,  F02C7/18 ,  F02C9/18 ,  F02K3/06

CPC classification number: F02C7/143 ,  F02C6/08 ,  F02C7/185 ,  F02C7/32 ,  F02C9/18 ,  F02K3/06 ,  F05D2220/3218 ,  F05D2220/323 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system.

公开(公告)号：US20180162537A1

公开(公告)日：2018-06-14

申请号：US15665860

申请日：2017-08-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  Brian Merry ,  Charles E. Lents ,  Stephen H. Taylor

IPC: B64D13/08 ,  F02C6/08 ,  F02K3/06 ,  F02C3/04 ,  F02C9/18 ,  F01D15/10 ,  H02K7/18 ,  B64D27/10

Abstract: An aircraft has a gas turbine engine including a compressor section that includes at least one compressor bleed. An environmental control system has an air input configured to receive pressurized cabin air. An intercooler has an input and an output. A selection valve is configured to selectively connect the bleeds to an intercooler input. At least one auxiliary compressor is connected to the intercooler output. An output of at least one auxiliary compressors is connected to an ECS air input. A controller is configured to receive contemporaneous operational data, calculate minimum configuration requirements to satisfy environmental demands, and transmit calculated configuration requirements to at least the selection valve to achieve a desired pressure and temperature for the air downstream of the auxiliary compressor. A method for supplying engine air to an environmental control system and a system for use on a turbine engine powered aircraft are also disclosed.

公开(公告)号：US09976489B2

公开(公告)日：2018-05-22

申请号：US14107273

申请日：2013-12-16

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  F05D2260/40311

Abstract: A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. A bypass ratio is defined as a volume of air delivered as bypass flow compared to a volume of air delivered into the core housing. The overall pressure ratio is greater than or equal to about 45.0, and the bypass ratio is greater than or equal to about 11.0.

公开(公告)号：US09970388B2

公开(公告)日：2018-05-15

申请号：US15586386

申请日：2017-05-04

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02K1/76 ,  F02K1/72 ,  B64D33/04 ,  B64D29/00

CPC classification number: F02K1/763 ,  B23P19/04 ,  B64D29/00 ,  B64D33/04 ,  F02K1/60 ,  F02K1/605 ,  F02K1/62 ,  F02K1/64 ,  F02K1/72 ,  F05D2260/50 ,  Y10T29/49229

Abstract: A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.