公开(公告)号：US10378374B2

公开(公告)日：2019-08-13

申请号：US14672561

申请日：2015-03-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F01D25/24 ,  F01D25/14 ,  F01D17/00 ,  F02C5/12 ,  F01D11/24 ,  F02C7/25

Abstract: A gas turbine engine includes a fluid intake. A turbine section includes a turbine case. A firewall is located upstream of the turbine section. A conduit is configured to direct a fluid from the fluid intake to the turbine case. A valve is located on a first side of the firewall opposite from the turbine section and is configured to regulate a flow of the fluid through the conduit.

公开(公告)号：US10352274B2

公开(公告)日：2019-07-16

申请号：US15240104

申请日：2016-08-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K3/062 ,  B64D27/14 ,  B64C11/46 ,  F02C7/36 ,  F02C3/10

Abstract: An aircraft engine includes a gas powered turbine core. A first fan is connected to the turbine core via a shaft. The fan is positioned aft of the turbine. A second fan is connected to the first fan via a geared connection.

公开(公告)号：US20190154059A1

公开(公告)日：2019-05-23

申请号：US16251133

申请日：2019-01-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F04D29/58 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C3/13 ,  F02C7/18 ,  F02C9/18

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US10287024B2

公开(公告)日：2019-05-14

申请号：US15228359

申请日：2016-08-04

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64D27/14 ,  B64D33/04 ,  F01D5/02 ,  F01D9/02 ,  F02K3/062 ,  F04D29/32 ,  F02C3/10 ,  B64D33/02

Abstract: An aircraft engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan connected to the turbine via a shaft. The fan is positioned aft of the turbine, and the shaft is at least partially disposed in a fan inlet flowpath.

公开(公告)号：US10215101B2

公开(公告)日：2019-02-26

申请号：US15118565

申请日：2014-09-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C9/18 ,  F01D25/16 ,  F01D25/24 ,  F04D29/52 ,  F04D29/54 ,  F04D29/58 ,  F02C6/08 ,  F02C7/25 ,  F04D29/70 ,  F02C7/052

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：US10202856B2

公开(公告)日：2019-02-12

申请号：US14842404

申请日：2015-09-01

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Stephen K. Kramer ,  Jesse M. Chandler

IPC: F01D13/00 ,  F01D9/02 ,  F02C3/04 ,  F01D5/04 ,  F01D5/06 ,  F02C7/04 ,  F02C3/14 ,  F02C3/05 ,  F02C3/08 ,  F02C3/10

Abstract: A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.

公开(公告)号：US20190017405A1

公开(公告)日：2019-01-17

申请号：US16141372

申请日：2018-09-25

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F02C7/25 ,  F01D11/24 ,  F01D17/00 ,  F01D25/14 ,  F01D25/24 ,  F02C5/12

Abstract: An active clearance control assembly for a gas turbine engine includes a firewall, a fluid intake and an active clearance control manifold. A conduit is configured to direct a fluid from the fluid intake on a first axial side of the firewall through the firewall to at least one active clearance control manifold on a second axial side of the firewall. A valve is located on the first axial side of the firewall and is configured to regulate the flow of the fluid through the conduit.

公开(公告)号：US10180117B2

公开(公告)日：2019-01-15

申请号：US15230086

申请日：2016-08-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  T. David Bomzer

IPC: F02C3/04 ,  F02K1/62 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72 ,  F02K1/76 ,  F01D25/24 ,  F02K1/60

Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, 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 is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.

公开(公告)号：US20180339765A1

公开(公告)日：2018-11-29

申请号：US15606051

申请日：2017-05-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alan H. Epstein ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C23/02 ,  B64C21/00

Abstract: A propulsion system for an aircraft comprises at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans. An aircraft is also disclosed.

公开(公告)号：US20180298829A1

公开(公告)日：2018-10-18

申请号：US15490155

申请日：2017-04-18

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C9/18 ,  F02K3/06 ,  B64D27/14 ,  B64D33/02

Abstract: A gas turbine engine comprises a housing having an inlet leading to a fan rotor. A bypass door is mounted upstream of the inlet to the fan rotor, and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath the engine. An aircraft is also disclosed.