公开(公告)号：US20190120084A1

公开(公告)日：2019-04-25

申请号：US16227271

申请日：2018-12-20

Applicant: United Technologies Corporation

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

IPC: F01D25/16 ,  F02K3/06 ,  F02C7/36 ,  F04D25/02 ,  F04D29/056 ,  F02C7/06 ,  F04D19/02 ,  F04D29/32 ,  F04D27/00 ,  F04D25/04 ,  F01D9/04 ,  F01D5/06 ,  F01D15/12 ,  F02C3/107 ,  F04D29/66 ,  F02C7/20

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. 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：US20190107058A1

公开(公告)日：2019-04-11

申请号：US16152710

申请日：2018-10-05

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C7/20 ,  F02C7/32 ,  F02C3/10 ,  F02C3/107

Abstract: An example gas turbine engine includes a propulsor assembly including a fan and a fan drive turbine. A weight of the propulsor assembly is less than about 40% of a total weight of the gas turbine engine.

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：US10202941B2

公开(公告)日：2019-02-12

申请号：US14441633

申请日：2013-03-04

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse Chandler

IPC: B64D27/00 ,  F02K1/64 ,  F02C3/045 ,  F02K3/06 ,  F02C6/00 ,  F02C3/04

Abstract: A gas turbine engine has a fan inlet and a fan configured to deliver air to an exhaust nozzle. A core gas turbine engine. including in serial order extending further into the engine, a core turbine section, a combustor and a core compressor section. A core engine inlet duct is spaced from the fan inlet. A method is also described.

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：US10196930B2

公开(公告)日：2019-02-05

申请号：US14974808

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Kurt J. Sobanski ,  Wesley K. Lord ,  William K. Ackermann

IPC: F01D25/10 ,  F01D25/12 ,  F02K3/115 ,  F02C7/18 ,  F02C7/32 ,  F02C3/04

Abstract: The present disclosure relates generally to a gas turbine engine that includes a fan configured to generate a fanstream and a fanstream duct configured to receive the fanstream flowing therethrough. An engine electronic component is positioned in flow communication with the fanstream. A heating element is positioned in the fanstream upstream from the engine electronic component and is operative to heat at least a portion of the fanstream in flow communication with the engine electronic component. The position of the engine electronic component passively thermally conditions the engine electronic component and the heating element actively thermally conditions the engine electronic component.

公开(公告)号：US20190017445A1

公开(公告)日：2019-01-17

申请号：US16025022

申请日：2018-07-02

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02K3/06 ,  F02C9/18 ,  F01D11/12 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F02K3/075 ,  F02C3/107

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a first compressor section and a second compressor section, the second compressor section including a second compressor section inlet with a compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, and a turbine having a first turbine section driving the first compressor section, a second turbine section driving the fan through an epicyclic gearbox, the second turbine section including blades and vanes, and wherein the second turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

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：US20180347815A1

公开(公告)日：2018-12-06

申请号：US16001349

申请日：2018-06-06

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill

IPC: F23R3/10 ,  F02C7/18 ,  F01D25/12 ,  F01D9/06 ,  F01D5/08 ,  F02C3/04 ,  F02C6/08

Abstract: A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system.