公开(公告)号：US20180209342A1

公开(公告)日：2018-07-26

申请号：US15412203

申请日：2017-01-23

Applicant: United Technologies Corporation

Inventor： Matthew Robert Pearson ,  Gabriel L. Suciu ,  Justin R. Urban

IPC: F02C7/12 ,  F02C3/04 ,  F28D15/02 ,  F28D15/04

Abstract: A gas turbine engine includes a rotor section proximate to a combustor section, where the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine also includes a heat pipe system. The heat pipe system includes one or more heat pipes installed between an upper portion of the rotor section and a lower portion of the rotor section. The heat pipe system is operable to accept heat at a hot side of the heat pipe system at the upper portion, flow heat from the hot side to a cold side of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion to reduce a thermal differential between the upper portion and the lower portion at engine shutdown.

公开(公告)号：US20180202366A1

公开(公告)日：2018-07-19

申请号：US15409889

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 ,  F02C7/06 ,  F02C7/36

CPC classification number: F02C7/32 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/76 ,  F05D2240/50 ,  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 set of gears and a second set of gears, the first towershaft extending into a housing and coupled to the first set of gears, the second towershaft extending into the housing and coupled to the second set of gears, an electric machine, and a transmission coupling the electric machine to the first set of gears, the transmission transitionable between a first mode where the electric machine is driven at a first speed relative to the first towershaft, and a second mode where the electric machine is driven at a different, second speed relative to the first towershaft.

公开(公告)号：US20180202310A1

公开(公告)日：2018-07-19

申请号：US15410049

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: F01D15/12 ,  F02C7/268 ,  F01D5/06 ,  F01D15/10 ,  F01D25/20 ,  F16H3/30

Abstract: An exemplary gas turbine engine assembly includes a transmission coupling a starter generator assembly to a 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：US20180163665A1

公开(公告)日：2018-06-14

申请号：US15880717

申请日：2018-01-26

Applicant: United Technologies Corporation

Inventor： Christopher A. Eckett ,  Gabriel L. Suciu

IPC: F02K3/075

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 that drives 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：US20180163633A1

公开(公告)日：2018-06-14

申请号：US15373072

申请日：2016-12-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/36 ,  B64D27/16

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

公开(公告)号：US20180149036A1

公开(公告)日：2018-05-31

申请号：US15881240

申请日：2018-01-26

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 ,  F01D5/06 ,  F04D29/053 ,  F04D25/04 ,  F02K3/06 ,  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 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：US09982599B2

公开(公告)日：2018-05-29

申请号：US14443145

申请日：2013-06-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/052 ,  B01D46/00 ,  F02C7/12

CPC classification number: F02C7/052 ,  B01D46/0023 ,  F02C7/12 ,  F05D2220/327 ,  F05D2260/40311 ,  F05D2260/607 ,  Y02T50/675

Abstract: A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.

公开(公告)号：US20180128168A1

公开(公告)日：2018-05-10

申请号：US15843012

申请日：2017-12-15

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Frederick M. Schwarz

IPC: F02C3/107 ,  F02C3/067 ,  F02C3/06 ,  F01D5/06 ,  F01D1/10 ,  F01D1/26 ,  F02C3/073 ,  F01D15/12

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second direction.

公开(公告)号：US09944401B2

公开(公告)日：2018-04-17

申请号：US14646752

申请日：2013-03-15

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: B64D33/04 ,  B64D27/20 ,  F02K1/60 ,  B64C5/02 ,  B64D27/14

CPC classification number: B64D33/04 ,  B64C5/02 ,  B64D27/14 ,  B64D27/20 ,  F02K1/60

Abstract: An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser includes an upper blocker door movable about a first pivot axis to a deployed position and a lower blocker door movable about a second pivot axis not parallel to the first pivot axis.

公开(公告)号：US09932905B2

公开(公告)日：2018-04-03

申请号：US14745606

申请日：2015-06-22

Applicant: United Technologies Corporation

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

IPC: F02C9/00 ,  F02C9/18 ,  F02K3/115 ,  F02C6/08 ,  F02C7/14 ,  F02C7/06

CPC classification number: F02C9/18 ,  F02C6/08 ,  F02C7/06 ,  F02C7/14 ,  F02K3/115 ,  F05D2230/31 ,  F05D2260/213 ,  Y02T50/675

Abstract: A gas turbine engine comprises a main fan that delivers air into a bypass duct and into a core engine. A heat exchanger is positioned within the bypass duct and receives a fluid to be cooled from a component associated with the gas turbine engine. A heat exchanger fan is positioned to draw air across the heat exchanger and a control for the heat exchanger fan. The control is programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions. A method of forming a heat exchanger is also disclosed.