公开(公告)号：US10144519B2

公开(公告)日：2018-12-04

申请号：US14887932

申请日：2015-10-20

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: B64D13/06 ,  F02C3/04 ,  F02K3/04 ,  F02K3/06 ,  F02C7/18 ,  F02C7/36 ,  F02K3/00 ,  F02C6/08 ,  F02C3/06 ,  F02C3/107 ,  F02C7/12 ,  F02C9/18

Abstract: A gas turbine engine includes a fan, a compressor section having at least two sequential compressors, a combustor section fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. The turbine section includes at least a first turbine, a second turbine and a third turbine. One of the first turbine, the second turbine and the third turbine is a fan-drive turbine. An environmental control system air supply includes at least a first compressor bleed and a second compressor bleed. Each of the first compressor bleed and the second compressor bleed are positioned upstream of a highest pressure compressor of the at least two compressors.

公开(公告)号：US20180339765A1

公开(公告)日：2018-11-29

申请号：US15606051

申请日：2017-05-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alan H. Epstein ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C23/02 ,  B64C21/00

Abstract: A propulsion system for an aircraft comprises at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans. An aircraft is also disclosed.

公开(公告)号：US20180320542A1

公开(公告)日：2018-11-08

申请号：US15589009

申请日：2017-05-08

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D11/24

Abstract: A clearance control system for a gas turbine engine comprises at least one case support associated with an engine case defining an engine center axis. A clearance control ring is positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring. The clearance control ring includes a first mount feature. An outer air seal has a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature. An injection source inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.

公开(公告)号：US20180313266A1

公开(公告)日：2018-11-01

申请号：US16027496

申请日：2018-07-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Nathan Snape ,  Christopher M. Dye

IPC: F02C3/04 ,  F02C7/14 ,  F01D25/12 ,  F02C7/32 ,  F02C7/06 ,  F02C7/12 ,  F01D25/18

CPC classification number: F02C3/04 ,  F01D25/12 ,  F01D25/18 ,  F02C7/06 ,  F02C7/12 ,  F02C7/14 ,  F02C7/32

Abstract: A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.

公开(公告)号：US20180306043A1

公开(公告)日：2018-10-25

申请号：US16017110

申请日：2018-06-25

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Simon Pickford ,  William K. Ackermann ,  Nathan Snape

IPC: F01D9/06 ,  F01D9/02 ,  F01D5/02 ,  F01D1/02 ,  F02C7/047 ,  F02C7/32 ,  F02C7/18 ,  F01D25/12 ,  F02C7/04

CPC classification number: F01D9/065 ,  F01D1/02 ,  F01D5/02 ,  F01D9/02 ,  F01D25/12 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32 ,  F05D2220/30 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/675

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.

公开(公告)号：US20180298829A1

公开(公告)日：2018-10-18

申请号：US15490155

申请日：2017-04-18

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C9/18 ,  F02K3/06 ,  B64D27/14 ,  B64D33/02

Abstract: A gas turbine engine comprises a housing having an inlet leading to a fan rotor. A bypass door is mounted upstream of the inlet to the fan rotor, and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath the engine. An aircraft is also disclosed.

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：US10060354B2

公开(公告)日：2018-08-28

申请号：US15445521

申请日：2017-02-28

Applicant: United Technologies Corporation

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

IPC: B64D27/10 ,  F02C7/20 ,  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：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.