公开(公告)号：US09822734B2

公开(公告)日：2017-11-21

申请号：US14184368

申请日：2014-02-19

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02K1/72 ,  F02K1/60 ,  F02K1/62 ,  F02K1/64 ,  B64D29/00 ,  B23P19/04 ,  F02K1/76

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: One embodiment includes a pivot thrust reverser. The pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axes that are each positionally fixed axes relative to the gas turbine engine assembly. A second tandem pivot door subassembly is included, spaced from the first tandem pivot door subassembly and comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axes that are each positionally fixed axes relative to the gas turbine engine assembly.

公开(公告)号：US20170306849A1

公开(公告)日：2017-10-26

申请号：US15137509

申请日：2016-04-25

Applicant: United Technologies Corporation

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

IPC: F02C7/24 ,  F02C3/04

CPC classification number: F02C7/24 ,  F02C3/04 ,  F02C7/25 ,  F02C7/32 ,  F05D2220/32 ,  F05D2230/51 ,  F05D2230/60

Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side, the second side having a lower operating temperature than the first side. A cover plate is installed over the module opening after the electronic module is inserted therethrough.

公开(公告)号：US20170276147A1

公开(公告)日：2017-09-28

申请号：US15079409

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F04D29/56 ,  F04D29/58 ,  F04D29/54

CPC classification number: F04D29/563 ,  F01D9/04 ,  F01D9/042 ,  F01D17/12 ,  F01D17/14 ,  F01D17/162 ,  F01D25/34 ,  F05D2220/32 ,  F05D2270/62 ,  Y02T50/671 ,  Y02T50/673

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

公开(公告)号：US20170276016A1

公开(公告)日：2017-09-28

申请号：US15079469

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F01D17/16 ,  F16H37/12 ,  F16H55/17 ,  F16H49/00 ,  F16H19/00

CPC classification number: F01D17/162 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2250/14 ,  F05D2260/53 ,  F05D2260/532 ,  F05D2260/57 ,  F16H19/001 ,  F16H37/12 ,  F16H49/001 ,  F16H55/17 ,  Y02T50/671

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

公开(公告)号：US20170276014A1

公开(公告)日：2017-09-28

申请号：US15079432

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F01D17/16 ,  F16H49/00

CPC classification number: F01D17/162 ,  F01D7/00 ,  F01D9/04 ,  F01D9/042 ,  F01D17/12 ,  F01D17/14 ,  F01D17/165 ,  F01D25/34 ,  F04D29/323 ,  F04D29/563 ,  F05D2220/32 ,  F05D2240/128 ,  F16H49/001 ,  Y02T50/671 ,  Y02T50/673

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

公开(公告)号：US20170276013A1

公开(公告)日：2017-09-28

申请号：US15079417

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jonathan F. Zimmitti ,  Jesse M. Chandler

IPC: F01D17/16 ,  F16H19/00 ,  F16H49/00

CPC classification number: F01D17/162 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/57 ,  F16H19/001 ,  F16H49/001 ,  Y02T50/671 ,  Y02T50/673

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

公开(公告)号：US09771863B2

公开(公告)日：2017-09-26

申请号：US14600304

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler ,  Stephen G. Pixton

IPC: B64D27/12 ,  F02C3/10 ,  F02K1/54 ,  F02C6/20 ,  F02C7/36 ,  B64D35/04

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C6/206 ,  F02C7/36 ,  F02K1/54

Abstract: An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.

公开(公告)号：US20170234267A1

公开(公告)日：2017-08-17

申请号：US15586386

申请日：2017-05-04

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

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

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.

公开(公告)号：US09663239B2

公开(公告)日：2017-05-30

申请号：US14440718

申请日：2013-03-14

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K1/54 ,  B64D33/04 ,  B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  F02K1/62

CPC classification number: B64D33/04 ,  B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  F02K1/54 ,  F02K1/62

Abstract: An aircraft includes a fuselage including a propulsion system supported within an aft portion. A thrust reverser is mounted proximate to the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser directs thrust at an angle relative to a vertical plane to reduce interference on control surfaces and reduce generation of underbody lift.

公开(公告)号：US09617009B2

公开(公告)日：2017-04-11

申请号：US14187021

申请日：2014-02-21

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F01D25/24 ,  B64D29/06 ,  F01D25/28 ,  F01D9/02

CPC classification number: B64D29/06 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/128 ,  F05D2240/1281 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2240/91 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/34 ,  F05D2250/75 ,  F05D2260/96 ,  Y10T29/49721

Abstract: A gas turbine engine includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion, and a fore bi-fi. The rail is coupled to the fore pylon portion and extending in the aft direction from the stationary portion. The second annular portion is arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion comprises an aft bi-fi configured to engage with the fore bi-fi when the gas turbine engine is in the closed position.