公开(公告)号：US10190497B2

公开(公告)日：2019-01-29

申请号：US14887433

申请日：2015-10-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: F01D1/26 ,  F02C7/36 ,  F02K1/78 ,  F01D25/30 ,  F02C3/107 ,  F02K3/072

Abstract: A gas turbine engine comprises a compressor section, a combustor section downstream of the compressor section, and a turbine section downstream of the combustor section. A mid-turbine frame includes an outer case portion and is configured to support the turbine section. At least one shaft defines an axis of rotation, and the turbine section comprises an inner rotor directly driving the shaft. The inner rotor includes an inner set of blades. An outer rotor is positioned immediately adjacent to the outer case portion and has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system is positioned downstream of the combustor section, is mounted to the mid-turbine frame, and is coupled to the outer rotor to drive the at least one shaft.

公开(公告)号：US10184402B2

公开(公告)日：2019-01-22

申请号：US15947890

申请日：2018-04-09

Applicant: United Technologies Corporation

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

IPC: F02C7/20 ,  F01D9/04 ,  F01D25/30 ,  F02K1/04

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a CMC turbine exhaust case mounted to the turbine case. The CMC turbine exhaust case includes a CMC core nacelle aft portion, a CMC tail cone connected to the CMC core nacelle aft portion, and a multiple of CMC turbine exhaust case struts extending between the CMC core nacelle aft portion and the CMC tail cone. The CMC core nacelle aft portion, the CMC tail cone and the turbine case are arranged along the turbine axis. The CMC turbine exhaust case is mounted to the turbine case at a flange such that the CMC tail cone is axially spaced apart from the turbine case relative to the turbine axis.

公开(公告)号：US20190017446A1

公开(公告)日：2019-01-17

申请号：US16025038

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 a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a first compressor section and a second compressor, the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, a shaft assembly having a first portion and a second portion, a turbine in fluid communication with the combustor, the turbine having a first turbine section coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section coupled to the second portion of the shaft assembly to drive the fan, an epicyclic transmission coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine to turn faster than the fan, wherein the second turbine section includes a maximum gas path radius and the fan blades include 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：US10156188B2

公开(公告)日：2018-12-18

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: F02C1/00 ,  F02C7/24 ,  F02C3/04 ,  F02C7/25 ,  F02C7/32

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：US10138751B2

公开(公告)日：2018-11-27

申请号：US14733984

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/00 ,  F01D11/12 ,  F01D11/00 ,  F01D5/06

Abstract: A seal segment according to an exemplary aspect of the present disclosure includes, among other things, a first axial wall, a second axial wall radially spaced from the first axial wall and a radially outer wall that interconnects the first axial wall and the second axial wall. At least one curved member is radially inwardly offset from the radially outer wall and extending between the first and second axial walls.

公开(公告)号：US10100745B2

公开(公告)日：2018-10-16

申请号：US14432377

申请日：2013-02-08

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/26 ,  F02C7/36 ,  F02C7/32 ,  F02C3/10 ,  F02C3/107 ,  F02C7/20

Abstract: An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.

公开(公告)号：US10093424B2

公开(公告)日：2018-10-09

申请号：US14998001

申请日：2014-07-07

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: B64D13/06 ,  B64D27/26 ,  F02K3/04

Abstract: A gas turbine engine includes a fan section delivering air into a compressor section. The compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. A pylon supports the engine. The pylon defines a lowermost surface and the higher pressure tap extends above a plane including the lowermost surface. The higher pressure tap includes a double wall tube above the plane for preventing leakage from impinging on a portion of the pylon. An environmental control system is also disclosed.

公开(公告)号：US10087886B2

公开(公告)日：2018-10-02

申请号：US14284893

申请日：2014-05-22

Applicant: United Technologies Corporation

Inventor： Allan R. Penda ,  Gabriel L. Suciu ,  William G. Sheridan ,  Wesley K. Lord

IPC: F02K1/70 ,  F02C7/36 ,  F02K1/32 ,  F02K3/075 ,  F02C3/10 ,  F02C3/113 ,  F02C3/14 ,  F02C6/04 ,  F16H3/60

Abstract: A gas turbine engine comprises a core engine, a fan, a bypass duct and a clutch. The fan is driven by the core engine. The bypass duct is configured to receive airflow from the fan. The clutch links the core engine and the fan. The core comprises a reverse-flow, two-spool gas generator in one embodiment. In another embodiment, the fan is driven by a free turbine aerodynamically powered by the core engine. In one embodiment, the clutch includes reverse gearing to reverse rotational output of the fan. In one embodiment, the clutch and reverse gearing are implemented in an epicyclic gear system.

公开(公告)号：US20180258859A1

公开(公告)日：2018-09-13

申请号：US15978455

申请日：2018-05-14

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02C7/143 ,  F01D25/12 ,  F02C3/13

CPC classification number: F02C7/185 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/143 ,  F02C7/32 ,  F02K3/115 ,  F05D2210/44 ,  F05D2220/3212 ,  F05D2220/3218 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  Y02T50/675 ,  Y02T50/676

Abstract: A gas turbine engine includes a main compressor. A tap is fluidly connected downstream of the main compressor. A heat exchanger is fluidly connected downstream of the tap. An auxiliary compressor unit is fluidly connected downstream of the heat exchanger. The auxiliary compressor unit is configured to compress air cooled by the heat exchanger with an overall auxiliary compressor unit pressure ratio between 1.1 and 6.0. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US20180237147A1

公开(公告)日：2018-08-23

申请号：US15439988

申请日：2017-02-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64D27/26 ,  B64D27/20 ,  B64D35/04

CPC classification number: B64D27/26 ,  B64D27/20 ,  B64D35/04 ,  B64D2027/268

Abstract: A propulsor and mount arrangement comprises a propulsor rotor and a fan casing surrounding the propulsor rotor. The fan casing receives two side mounts and a thrust link pivotally attached to the fan casing at a location that will be within 10° of a vertically lowermost location when the propulsor is mounted on an aircraft, and the side mounts being at circumferentially opposed positions, and within a lower 270° when the propulsor is mounted on an aircraft. At least a portion of both the side mounts, and a pivot point connect the thrust link to the fan casing in a common plane defined perpendicular to a rotational axis of the propulsor rotor. An aircraft is also disclosed.