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：US10422243B2

公开(公告)日：2019-09-24

申请号：US15410049

申请日：2017-01-19

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F01D15/12 ,  F02C7/268 ,  F01D5/06 ,  F01D15/10 ,  F01D25/20 ,  F16H3/30 ,  F02C7/277 ,  F02C7/32 ,  F02C7/36

Abstract: An exemplary gas turbine engine assembly includes a transmission coupling a starter generator assembly to a first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.

公开(公告)号：US10415596B2

公开(公告)日：2019-09-17

申请号：US15079382

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M Chandler

IPC: F04D29/56 ,  F04D27/00 ,  F01D9/04 ,  F01D17/12 ,  F01D17/14 ,  F01D17/16 ,  F01D25/34

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine. A drive arm is driven by the harmonic drive to drive a unison ring. A multiple of variable vanes driven by the unison ring.

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：US10309310B2

公开(公告)日：2019-06-04

申请号：US14758277

申请日：2013-05-10

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C6/08 ,  F02C7/18 ,  F02K3/02 ,  F02K3/00 ,  F02C9/18 ,  F02C3/13 ,  F02C3/14 ,  F02C6/04

Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.

公开(公告)号：US20190162118A1

公开(公告)日：2019-05-30

申请号：US16264837

申请日：2019-02-01

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/18 ,  F02K3/06 ,  F02K3/062 ,  F02C9/18 ,  F01D25/12 ,  F02C6/08

CPC classification number: F02C7/18 ,  B64D2013/0603 ,  F01D25/12 ,  F02C6/08 ,  F02C9/18 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/327 ,  F05D2250/51 ,  Y02T50/675

Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.

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：US20190055888A1

公开(公告)日：2019-02-21

申请号：US16047634

申请日：2018-07-27

Applicant: United Technologies Corporation

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

IPC: F02C7/20 ,  B64D27/10 ,  B64D27/26

CPC classification number: F02C7/20 ,  B64D27/10 ,  B64D27/26 ,  B64D2027/262 ,  B64D2027/266 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/90 ,  Y02T50/44 ,  Y10T29/49947

Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.

公开(公告)号：US20190048803A1

公开(公告)日：2019-02-14

申请号：US16025094

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

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.