公开(公告)号：US10112696B2

公开(公告)日：2018-10-30

申请号：US14440887

申请日：2013-03-15

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: B64C1/26 ,  B64C5/02 ,  B64D25/00 ,  B64D27/20 ,  B64D33/02 ,  B64C1/06

Abstract: An aircraft assembly is disclosed and includes a fuselage including a turbine engine mounted within the aft fuselage. A burst zone is defined about the turbine engine and a tail is disposed at least partially with the burst zone. The tail includes primary control surfaces and sacrificial control surfaces. The sacrificial control surfaces can break away in a defined manner to maintain integrity of the primary control surfaces outside of the burst zone.

公开(公告)号：US20180258860A1

公开(公告)日：2018-09-13

申请号：US15978517

申请日：2018-05-14

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02C3/04 ,  F02C7/32

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323 ,  F05D2240/90 ,  F05D2260/213 ,  F05D2260/4031

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A tap connects to the compressor section. A heat exchanger connects downstream of the tap. A cooling compressor connects downstream of the heat exchanger, and the cooling compressor connects to deliver air to at least one of the rotating components. A core housing has an outer peripheral surface and a fan housing defines an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is disposed within the at least one bifurcation duct.

公开(公告)号：US10060357B2

公开(公告)日：2018-08-28

申请号：US15292472

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F01D11/12

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 has 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.

公开(公告)号：US20180209339A1

公开(公告)日：2018-07-26

申请号：US15925811

申请日：2018-03-20

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C6/08 ,  F02C7/32 ,  B64D13/04 ,  F02C9/18 ,  B64D13/06

CPC classification number: F02C6/08 ,  B64D13/04 ,  B64D2013/0644 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323

Abstract: An environmental control system includes a low pressure tap at a location on a first compressor section of a main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use.

公开(公告)号：US20180202368A1

公开(公告)日：2018-07-19

申请号：US15410113

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: F02C7/32 ,  F02C3/06 ,  F02C7/18 ,  F02C7/36 ,  F02C7/268 ,  F01D15/10 ,  F01D15/12 ,  F01D25/12 ,  F16H1/22 ,  H02K7/116 ,  H02K7/18

CPC classification number: F02C7/32 ,  F01D15/10 ,  F01D15/12 ,  F01D25/12 ,  F02C3/06 ,  F02C7/185 ,  F02C7/268 ,  F02C7/275 ,  F02C7/36 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2260/85 ,  F16H1/222 ,  H02K7/116 ,  H02K7/1823

Abstract: An exemplary gas turbine engine assembly includes a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second turbines are mounted for rotation about a common rotational axis within an engine static structure. The first and second turbine shafts are coaxial with one another. First and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox has a set of gears. A compressor is driven by the first towershaft. The engine assembly further includes a starter generator assembly, and a transmission coupling the starter generator assembly to the 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：US20180202367A1

公开(公告)日：2018-07-19

申请号：US15409974

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: F02C7/32 ,  F02C7/277 ,  F02C7/22 ,  F01D15/10 ,  F01D15/08 ,  F01D15/12 ,  F01D5/06 ,  F01D25/20 ,  F01D25/16

CPC classification number: F02C7/32 ,  F01D5/06 ,  F01D15/08 ,  F01D15/10 ,  F01D15/12 ,  F01D25/16 ,  F01D25/20 ,  F02C7/22 ,  F02C7/277 ,  F02C7/36 ,  F05D2220/32 ,  F05D2220/50 ,  F05D2240/60 ,  F05D2260/4031

Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first gear train and a second gear train, the first towershaft extending into a housing and coupled to the first gear train, the second towershaft extending into the housing and coupled to the second gear train, a hydraulic pump, a transmission coupling the hydraulic pump to the first gear train, the transmission transitionable between a first mode where the hydraulic pump is driven at a first speed relative to the first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.

公开(公告)号：US20180163664A1

公开(公告)日：2018-06-14

申请号：US15373101

申请日：2016-12-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K3/062

CPC classification number: F02K3/062 ,  B64D27/10 ,  B64D35/04 ,  B64D35/08 ,  F01D13/003 ,  F02C3/107 ,  F05D2250/312

Abstract: A propulsion system for an aircraft has at least two fans, each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans, and drive an output shaft which drives a gear to, in turn, engage for driving a gear on a first intermediate shaft extending from the turboshaft gas turbine engine in a rearward direction toward an intermediate fan drive shaft. The intermediate fan drive shaft drives ng the fan drive shaft, and the first intermediate shafts extending over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine and the fan than in a width dimension defined between the at least two fans. The first intermediate shafts are concentric.

公开(公告)号：US20180135454A1

公开(公告)日：2018-05-17

申请号：US15856396

申请日：2017-12-28

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D15/12 ,  F04D25/04 ,  F02K3/06 ,  F04D29/053 ,  F01D5/06 ,  F04D19/00

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 according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral stiffness and the ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness the ring gear transverse stiffness.

公开(公告)号：US20180119564A1

公开(公告)日：2018-05-03

申请号：US15856441

申请日：2017-12-28

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D15/12 ,  F02K3/06 ,  F04D29/053 ,  F04D25/04 ,  F04D19/00 ,  F01D5/06

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 according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A gear system input connected to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness At least one of the gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.

公开(公告)号：US20180106194A1

公开(公告)日：2018-04-19

申请号：US15784629

申请日：2017-10-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian Merry ,  Gabriel L. Suciu ,  James W. Norris

IPC: F02C3/073 ,  F02K3/068 ,  F02K1/04

CPC classification number: F02C3/073 ,  F02K1/04 ,  F02K3/068 ,  F05D2300/603 ,  F05D2300/614 ,  Y02T50/672 ,  Y10T29/49346

Abstract: A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.