公开(公告)号：US10472081B2

公开(公告)日：2019-11-12

申请号：US15874335

申请日：2018-01-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord

IPC: B64D35/08 ,  B64C11/00 ,  B64C21/06 ,  B64C39/00 ,  B64C1/06 ,  B64D35/02 ,  B64C23/02 ,  B64C5/02 ,  F04D17/04 ,  B64D27/02 ,  B64D41/00

Abstract: A cross flow fan to be incorporated into an aircraft fuselage comprises an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface, and a drive arrangement for the ingestion fan rotor. An aircraft is also disclosed.

公开(公告)号：US20190186381A1

公开(公告)日：2019-06-20

申请号：US16284671

申请日：2019-02-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C9/18 ,  F01D25/16 ,  F04D29/52 ,  F04D29/54 ,  F04D29/70 ,  F02C7/25 ,  F02C6/08 ,  F01D25/24 ,  F04D29/58

CPC classification number: F02C9/18 ,  F01D25/162 ,  F01D25/24 ,  F02C6/08 ,  F02C7/052 ,  F02C7/25 ,  F04D29/522 ,  F04D29/542 ,  F04D29/5853 ,  F04D29/701 ,  F05D2220/32 ,  F05D2240/15

Abstract: A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port.

公开(公告)号：US20190032518A1

公开(公告)日：2019-01-31

申请号：US15662318

申请日：2017-07-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F01D25/28 ,  F02K3/06 ,  B64D27/12 ,  B64D27/26

Abstract: A gas turbine engine according to an example of the present disclosure includes a mount arrangement including a gas turbine engine, an adapter ring extending circumferentially around the gas turbine engine and mounted to both the gas turbine engine and to an aircraft beneath the gas turbine engine, and at least one thrust link including a first end mounted to the gas turbine engine fore of the adapter ring, and an opposite second end mounted to the adapter ring above the gas turbine engine.

公开(公告)号：US20180363492A1

公开(公告)日：2018-12-20

申请号：US16059377

申请日：2018-08-09

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Federico Papa

IPC: F01D17/14 ,  F02C3/04 ,  F02C9/18 ,  F02C7/18 ,  F01D25/26

Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

公开(公告)号：US10060350B2

公开(公告)日：2018-08-28

申请号：US14685325

申请日：2015-04-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Harold W. Hipsky ,  Thomas M. Zywiak

IPC: F02C7/04 ,  B64C11/14 ,  F01D25/12 ,  F02C7/14 ,  F02C7/18

CPC classification number: F02C7/04 ,  B64C11/14 ,  F01D25/12 ,  F02C7/14 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/213

Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.

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：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：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：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.

公开(公告)号：US20180051627A1

公开(公告)日：2018-02-22

申请号：US15239086

申请日：2016-08-17

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02C3/10 ,  F02C7/36 ,  F01D25/30 ,  F02K3/12 ,  B64D27/10 ,  B64D33/04 ,  B64D33/02

CPC classification number: F02C3/10 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  F01D25/30 ,  F02C7/36 ,  F02K3/062 ,  F02K3/12 ,  F05D2220/32 ,  F05D2250/314 ,  F05D2260/40311

Abstract: A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.