公开(公告)号：US09797311B2

公开(公告)日：2017-10-24

申请号：US14729800

申请日：2015-06-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Allan R. Penda ,  Brian D. Merry ,  Christopher M. Dye ,  Nathan Snape

IPC: F02C7/18 ,  F02C7/14 ,  F02C7/08

CPC classification number: F02C7/185 ,  F02C7/08 ,  F02C7/14 ,  F02C7/18 ,  Y02T50/671

Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.

公开(公告)号：US20170284298A1

公开(公告)日：2017-10-05

申请号：US15091186

申请日：2016-04-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Kurt J. Sobanski ,  William K. Ackermann

IPC: F02C7/18 ,  F02K3/065

Abstract: A low pressure compressor for a gas turbine engine includes a low pressure compressor case extending circumferentially around a central axis of the gas turbine engine. The low pressure compressor case includes an inner radial wall surrounding a low pressure compressor rotor and an outer radial wall at least partially defining a fan bypass passage of the gas turbine engine. A low pressure compressor compartment is located between the inner radial wall and the outer radial wall and an electrical component is located in the low pressure compressor compartment. An inlet port at the outer radial wall is configured to admit a cooling airflow into the low pressure compressor compartment from the fan bypass passage to cool the electrical component.

公开(公告)号：US20170276148A1

公开(公告)日：2017-09-28

申请号：US15079446

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F04D29/56 ,  F04D29/54

CPC classification number: F04D29/563 ,  F01D7/00 ,  F01D9/04 ,  F01D9/042 ,  F01D17/12 ,  F01D17/14 ,  F01D17/162 ,  F01D17/165 ,  F02B37/24 ,  F04D29/323 ,  F04D29/542 ,  F05D2220/32 ,  F05D2270/62 ,  Y02T50/671 ,  Y02T50/673

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

公开(公告)号：US20170276146A1

公开(公告)日：2017-09-28

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

CPC classification number: F04D29/563 ,  F01D9/04 ,  F01D9/042 ,  F01D17/12 ,  F01D17/14 ,  F01D17/162 ,  F01D25/34 ,  F04D27/002 ,  Y02T50/671 ,  Y02T50/673

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

公开(公告)号：US20170276018A1

公开(公告)日：2017-09-28

申请号：US15079505

申请日：2016-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anthony R. Bifulco ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F01D17/16

CPC classification number: F01D17/162 ,  F01D9/04 ,  F01D17/12 ,  F01D25/34 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/40 ,  F16H19/04 ,  F16H49/001 ,  Y02T50/671

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

公开(公告)号：US09752511B2

公开(公告)日：2017-09-05

申请号：US15484441

申请日：2017-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D25/00 ,  F02C7/36 ,  F04D25/04 ,  F04D29/32 ,  F01D5/06 ,  F01D9/04 ,  F01D15/12 ,  F02K3/06

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.

公开(公告)号：US09752510B2

公开(公告)日：2017-09-05

申请号：US15000077

申请日：2016-01-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Michael E. McCune ,  Brian D. Merry

IPC: F02C7/16 ,  F02C7/36 ,  F01D15/12 ,  F02C3/107 ,  F02C3/06

CPC classification number: F02C7/36 ,  F01D15/12 ,  F02C3/06 ,  F02C3/107 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/40 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.

公开(公告)号：US09739205B2

公开(公告)日：2017-08-22

申请号：US14573812

申请日：2014-12-17

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a combustor section located axially upstream of the drive turbine, and a speed change mechanism located axially downstream of the combustor section and axially upstream of the drive turbine. An output of the speed change mechanism connects to the fan.

公开(公告)号：US09694912B2

公开(公告)日：2017-07-04

申请号：US14187034

申请日：2014-02-21

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F01D25/24 ,  B64D29/06 ,  F01D25/28 ,  F01D9/02

CPC classification number: B64D29/06 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/128 ,  F05D2240/1281 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2240/91 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/34 ,  F05D2250/75 ,  F05D2260/96 ,  Y10T29/49721

Abstract: A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extending in the aft direction from the first annular portion. A second annular portion, aft of the first annular portion and coupled to the rail, is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion when the second annular portion is in the closed position, thereby providing access to the engine core. A guide pin extends forward from the second annular portion. A locking mechanism is disposed within the first annular portion for engaging the guide pin when the second annular portion is in the closed position.

公开(公告)号：US20170130289A1

公开(公告)日：2017-05-11

申请号：US15411355

申请日：2017-01-20

Applicant: United Technologies Corporation

Inventor： Dilip M. Shah ,  Herbert A. Chin ,  John Joseph Marcin ,  Paul L. Reynolds ,  Gabriel L. Suciu ,  Paul D. Genereux

IPC: C21D9/08 ,  C21D1/26 ,  B22D27/04 ,  C22C19/05 ,  C22C38/00 ,  C21D8/10 ,  C22F1/10

Abstract: High modulus turbine shafts and high modulus cylindrical articles are described as are the process parameters for producing these shafts and cylindrical articles. The shafts/articles have a high Young's modulus as a result of having high modulus crystal texture along the longitudinal axis of the shaft/article. The shafts are produced from directionally solidified seeded single crystal cylinders that are axisymmetrically hot worked before a limited recrystallization process is carried out at a temperature below the recrystallization temperature of the alloy. The disclosed process produces an intense singular texture and results in shaft or cylindrical article with a Young's modulus that is at least 40% greater than that of conventional nickel or iron alloys or conventional steels.