公开(公告)号：US20190323789A1

公开(公告)日：2019-10-24

申请号：US16502518

申请日：2019-07-03

Applicant: United Technologies Corporation

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

IPC: F41A9/63 ,  F02C3/04 ,  F02C7/18 ,  F02C7/32 ,  F41A9/65

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the 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, and delivers air into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US10451004B2

公开(公告)日：2019-10-22

申请号：US15173288

申请日：2016-06-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: F01D5/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  B64D27/26 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C9/20 ,  F02C9/18 ,  F01D9/02 ,  F02K1/15

Abstract: A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

公开(公告)号：US10364041B2

公开(公告)日：2019-07-30

申请号：US15218915

申请日：2016-07-25

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Arthur W. Utay ,  Tania Bhatia Kashyap ,  Thomas N. Slavens ,  Kevin L. Rugg ,  Mark F. Zelesky ,  Brian D. Merry ,  Gabriel L. Suciu

IPC: B64D41/00 ,  F04D17/10 ,  F02C3/08 ,  F02C3/14

Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

公开(公告)号：US10302014B2

公开(公告)日：2019-05-28

申请号：US14598269

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Brian D. Merry

IPC: F02C3/06

Abstract: A method comprises the steps of modifying an existing engine which includes a high pressure compressor driven by a high pressure turbine and a low pressure turbine to drive a low pressure compressor. The modifying step includes utilizing the high pressure compressor as a low pressure compressor in a modified gas turbine engine, and designing and incorporating a new high pressure compressor downstream of the low pressure compressor section in the modified engine, such that a portion of the design of the existing engine is utilized in the modified engine. A gas turbine engine is also disclosed.

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：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：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：US09988986B2

公开(公告)日：2018-06-05

申请号：US14600445

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  William Ackermann

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F05D2260/213

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

公开(公告)号：US09897040B2

公开(公告)日：2018-02-20

申请号：US14190171

申请日：2014-02-26

Applicant: United Technologies Corporation

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

IPC: F02K1/60

CPC classification number: F02K1/60 ,  F05D2210/40 ,  F05D2250/314

Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.