公开(公告)号：US09970322B2

公开(公告)日：2018-05-15

申请号：US14759986

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: F01D25/16 ,  B64D27/18 ,  F01D25/28 ,  F02C7/20 ,  B64D27/26

CPC classification number: F01D25/162 ,  B64D27/18 ,  B64D2027/264 ,  F01D25/28 ,  F02C7/20 ,  Y02T50/44 ,  Y02T50/671

Abstract: A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount. The first bearing supports at least a portion of the low pressure turbine section. The mid-turbine frame supports the first bearing. The rear mount is connected to the mid-turbine frame and is configured to react loads from the gas turbine engine.

公开(公告)号：US09920708B2

公开(公告)日：2018-03-20

申请号：US14617366

申请日：2015-02-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Nathan Snape ,  Anthony R. Bifulco ,  William K. Ackermann ,  Becky E. Rose ,  Jesse M. Chandler

IPC: F02C7/04 ,  F02K1/04 ,  F01D15/08 ,  F01D25/14 ,  F02C7/057 ,  F02C7/18 ,  F01D25/12 ,  F02C7/14

CPC classification number: F02K1/04 ,  F01D15/08 ,  F01D25/12 ,  F01D25/125 ,  F01D25/14 ,  F02C7/04 ,  F02C7/047 ,  F02C7/057 ,  F02C7/14 ,  F02C7/18 ,  F02C7/185 ,  F02C7/32 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.

公开(公告)号：US09915225B2

公开(公告)日：2018-03-13

申请号：US14615484

申请日：2015-02-06

Applicant: United Technologies Corporation

Inventor： Christopher A. Eckett ,  Gabriel L. Suciu

IPC: F02K3/075 ,  F02K1/72 ,  B64D29/06 ,  B64D27/26 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04 ,  F02K3/06

CPC classification number: F02K3/075 ,  B64D27/26 ,  B64D29/06 ,  B64D33/04 ,  B64D2027/266 ,  B64D2027/268 ,  F01D25/24 ,  F02C3/04 ,  F02K1/09 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F02K3/06 ,  F05D2240/14 ,  F05D2270/051 ,  Y02T50/671 ,  Y02T50/672

Abstract: A method of designing an engine according to an exemplary aspect of the present disclosure includes, among other things, designing an engine and a nacelle assembly together in an interactive process, the engine including a turbine section configured to drive a fan section and a compressor section. The step of designing the compressor section includes the step of designing a first compressor and a second compressor, with an overall pressure ratio being greater than or equal to about 35. The step of designing the nacelle assembly includes the step of designing the fan section to include a fan nacelle arranged at least partially about a fan, with the fan section having a fan pressure ratio of less than about 1.7. The step of designing the fan section includes configuring the fan section to deliver a portion of air into the compressor section, and a portion of air into a bypass duct, and with a bypass ratio equal to or greater than about 5.

公开(公告)号：US09915165B2

公开(公告)日：2018-03-13

申请号：US14751299

申请日：2015-06-26

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F01D17/00 ,  F02C6/08 ,  F02C7/32 ,  F01D25/28 ,  F02C3/04 ,  F02C3/14 ,  F02C7/20 ,  F02C7/36

CPC classification number: F01D17/00 ,  F01D25/28 ,  F02C3/04 ,  F02C3/14 ,  F02C6/08 ,  F02C7/20 ,  F02C7/32 ,  F02C7/36 ,  F02C9/18

Abstract: An environmental control system includes a higher pressure tap at a higher pressure location in the main 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 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 pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface. 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.

公开(公告)号：US09909495B2

公开(公告)日：2018-03-06

申请号：US14600487

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler ,  Michael Winter ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C3/10 ,  F02K3/00 ,  B64D27/12 ,  B64D35/04 ,  F02K3/077 ,  F02C3/107

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C3/107 ,  F02K3/00 ,  F02K3/077

Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US20180051654A1

公开(公告)日：2018-02-22

申请号：US15240104

申请日：2016-08-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

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

CPC classification number: F02K3/062 ,  B64C11/46 ,  B64D27/14 ,  F02C3/10 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/4031

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：US20180045138A1

公开(公告)日：2018-02-15

申请号：US14617366

申请日：2015-02-09

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Nathan Snape ,  Anthony R. Bifulco ,  William K. Ackermann ,  Becky E. Rose ,  Jesse M. Chandler

IPC: F02K1/04 ,  F01D25/14 ,  F01D25/12 ,  F02C7/14 ,  F02C7/18 ,  F01D15/08 ,  F02C7/057

CPC classification number: F02K1/04 ,  F01D15/08 ,  F01D25/12 ,  F01D25/125 ,  F01D25/14 ,  F02C7/04 ,  F02C7/047 ,  F02C7/057 ,  F02C7/14 ,  F02C7/18 ,  F02C7/185 ,  F02C7/32 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.

公开(公告)号：US09884674B2

公开(公告)日：2018-02-06

申请号：US14440995

申请日：2013-10-17

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C9/00 ,  B64C5/02 ,  B64D27/14 ,  B64C5/06 ,  B64C9/02 ,  B64C19/00 ,  B64D33/04 ,  F02K1/56 ,  F02K1/78 ,  B64C1/26

CPC classification number: B64C5/02 ,  B64C1/26 ,  B64C5/06 ,  B64C9/02 ,  B64C19/00 ,  B64D27/14 ,  B64D33/04 ,  F02K1/56 ,  F02K1/78

Abstract: An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at least one primary control surface. The primary control surfaces maintain aircraft controllability in the event that the sacrificial control surface becomes inoperable.

公开(公告)号：US09856793B2

公开(公告)日：2018-01-02

申请号：US14745564

申请日：2015-06-22

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Gabriel L. Suciu ,  Brian D. Merry

IPC: F02C6/04 ,  F02C6/08 ,  F02K3/115 ,  F02C7/143

CPC classification number: F02C6/08 ,  F02C7/143 ,  F02K3/115 ,  F05D2260/211 ,  Y02T50/676

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. The cooling compressor includes a downstream connection that delivers discharge pressure air to an upstream location in the high pressure turbine and a second tap from an intermediate pressure location within the cooling compressor. The second tap is connected to a downstream location within the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US20170370285A1

公开(公告)日：2017-12-28

申请号：US15682848

申请日：2017-08-22

Applicant: United Technologies Corporation

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

IPC: F02C3/113 ,  F02C3/06 ,  F02K3/06 ,  F02C7/36 ,  F02C9/16

CPC classification number: F02C3/113 ,  F02C3/06 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06 ,  F02K3/072 ,  F05D2200/221 ,  F05D2220/3215 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2270/20

Abstract: A compressor section is in fluid communication with a fan, which includes a first compressor section and a second compressor section. A turbine section includes a first turbine section driving the fan and the first compressor section and a second turbine section driving the second compressor section and the second compressor rotor. A first performance quantity is defined as a product of the first speed squared and the first area. A second performance quantity is defined as a product of the second speed squared and the second exit area. A performance ratio of the first performance quantity to the second performance quantity is between about 0.2 and about 0.8. A gear reduction is included between the first turbine section and the first compressor section.