公开(公告)号：US10371056B2

公开(公告)日：2019-08-06

申请号：US14964984

申请日：2015-12-10

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F01D25/08 ,  F01D5/02 ,  F02C7/36 ,  F02K3/06 ,  F01D5/08 ,  F02C6/08 ,  F02C7/12

Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.

公开(公告)号：US20190154059A1

公开(公告)日：2019-05-23

申请号：US16251133

申请日：2019-01-18

Applicant: United Technologies Corporation

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

IPC: F04D29/58 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C3/13 ,  F02C7/18 ,  F02C9/18

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main 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. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

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.

公开(公告)号：US10082078B2

公开(公告)日：2018-09-25

申请号：US14667975

申请日：2015-03-25

Applicant: United Technologies Corporation

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

IPC: F02C7/14

CPC classification number: F02C7/14 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/98 ,  Y02T50/671 ,  Y02T50/675

Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.

公开(公告)号：US10077666B2

公开(公告)日：2018-09-18

申请号：US14844082

申请日：2015-09-03

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D5/08 ,  F01D11/00 ,  F02C3/08 ,  F01D5/06

CPC classification number: F01D5/18 ,  F01D5/06 ,  F01D5/185 ,  F01D5/186 ,  F01D5/187 ,  F01D11/001 ,  F01D11/003 ,  F01D11/005 ,  F02C3/08 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/676

Abstract: A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.

公开(公告)号：US20180230912A1

公开(公告)日：2018-08-16

申请号：US15941240

申请日：2018-03-30

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D5/12 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C7/28 ,  F02K3/02 ,  F02C7/06

CPC classification number: F02C7/36 ,  F01D5/12 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2260/40 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes, among other things, a fan, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement drives the fan. A compressor section includes both a low pressure compressor and a high pressure compressor. A turbine section drives the gear arrangement. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor and a pressure ratio across the high pressure compressor, and greater than 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the high pressure compressor is greater than 7.

公开(公告)号：US10006370B2

公开(公告)日：2018-06-26

申请号：US14745539

申请日：2015-06-22

Applicant: United Technologies Corporation

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

IPC: F01D25/08 ,  F02C7/18

CPC classification number: F02C7/18 ,  F05D2260/213 ,  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. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.

公开(公告)号：US10006364B2

公开(公告)日：2018-06-26

申请号：US14813284

申请日：2015-07-30

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/06 ,  F02C7/12 ,  F01D5/08 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F01D11/00 ,  F01D25/12 ,  F04D29/32 ,  F04D29/16 ,  F04D29/54 ,  F04D29/58

CPC classification number: F02C7/12 ,  F01D5/066 ,  F01D5/084 ,  F01D5/087 ,  F01D11/001 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D29/164 ,  F04D29/321 ,  F04D29/545 ,  F04D29/584 ,  F05D2220/32 ,  F05D2260/221 ,  Y02T50/676

Abstract: A rotor for a gas turbine engine includes a cold shell, a hot shell, and a spoke. The spoke is connected to and extends radially outward from the cold shell. The hot shell is connected to the cold shell by the spoke and includes an axially extending outboard segment and an axially extending inboard segment. The outboard segment is connected to the inboard segment and the inboard segment is disposed radially inboard of the outboard segment for sealably engaging a stator blade shroud.

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：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.