公开(公告)号：US10233772B2

公开(公告)日：2019-03-19

申请号：US14770599

申请日：2014-03-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune

IPC: F01D21/04 ,  F02C7/06 ,  F01D21/08 ,  F01D5/02 ,  F01D15/12 ,  F01D17/06 ,  F01D25/16 ,  F01D25/24

Abstract: A gas turbine engine (20) and method for containing a fan inside an engine after a fan thrust bearing assembly failure. The engine (20) may comprise a fan (42), a housing (100) including a compartment (102), a fan shaft (104) inside the compartment (102) and comprising a bowl (108), a support structure (110) inside the compartment (102), a speed sensor pickup (114) mounted on the outer surface (120) of the bowl (108), a speed sensor (112) mounted on the support structure (110), and a fan thrust bearing assembly (41) disposed forward of the bowl (108). The fan thrust bearing assembly (41) including a bearing (126). The speed sensor (112) and the sensor pickup (114) define a defining a sensor gap (116). The bearing (126) and the outer surface (120) defining a fan thrust bearing gap (130), wherein the sensor gap (116) is less than the fan thrust bearing gap.

公开(公告)号：US10208624B2

公开(公告)日：2019-02-19

申请号：US14769015

申请日：2013-12-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Loc Quang Duong ,  Xiaolan Hu ,  Ernest Boratgis ,  Michael E. McCune

IPC: F01D25/20 ,  F02C7/36 ,  F16H57/04 ,  F01D25/18 ,  F02K3/06 ,  F02C3/107 ,  F01D5/02 ,  F01D15/08 ,  F01D15/12 ,  F01D25/16 ,  F04C2/344 ,  F04C13/00 ,  F04C15/00

Abstract: The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counter-clockwise.

公开(公告)号：US10202902B2

公开(公告)日：2019-02-12

申请号：US14899646

申请日：2014-08-22

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Zachary R. Nado

IPC: F16H57/04 ,  F02C3/107 ,  F02C7/36

Abstract: A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed.

公开(公告)号：US20180363665A1

公开(公告)日：2018-12-20

申请号：US15625144

申请日：2017-06-16

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F04D25/16 ,  F04D25/04 ,  F04D29/046 ,  F04D29/041 ,  F01D5/02 ,  F01D15/12 ,  F16H1/28 ,  F16H57/10

Abstract: A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

公开(公告)号：US20180171815A1

公开(公告)日：2018-06-21

申请号：US15827132

申请日：2017-11-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  William G. Sheridan ,  Michael E. McCune

IPC: F01D15/12 ,  F01D15/08 ,  F01D15/10 ,  F16H1/22 ,  F16H15/04 ,  F16H37/02

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D15/08 ,  F01D15/10 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/402 ,  F05D2260/4031 ,  F05D2270/024 ,  F16H1/222 ,  F16H15/04 ,  F16H37/021

Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, 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, an accessory drive gearbox a first towershaft interconnecting the accessory drive gearbox and the first or second turbine shaft, and a multispeed transmission interconnecting the accessory drive gearbox and at least one accessory component.

公开(公告)号：US20180094579A1

公开(公告)日：2018-04-05

申请号：US15828510

申请日：2017-12-01

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

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

CPC classification number: F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/403 ,  F05D2260/4031

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan delivering air into a bypass duct and into a core engine, a fan drive gear system having a gear carrier, and a fan shaft coupling the fan drive gear system to the fan. The core engine includes a low spool including a low pressure turbine and a low pressure shaft, and a high spool including a high pressure turbine, a compressor, and a high pressure shaft coupling the high pressure turbine to the compressor. A first bearing is forward of the fan drive gear system, and supporting said fan shaft and said fan drive gear system, and a second bearing is aft of the fan drive gear system, and supporting the fan drive gear system.

公开(公告)号：US09909495B2

公开(公告)日：2018-03-06

申请号：US14600487

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler ,  Michael Winter ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C3/10 ,  F02K3/00 ,  B64D27/12 ,  B64D35/04 ,  F02K3/077 ,  F02C3/107

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C3/107 ,  F02K3/00 ,  F02K3/077

Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US09896969B2

公开(公告)日：2018-02-20

申请号：US14663207

申请日：2015-03-19

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Marc J. Muldoon ,  Michael E. McCune

IPC: F01D25/18 ,  F16J15/16 ,  F16H57/04 ,  F16J15/42 ,  F01D25/16 ,  F01D11/02

CPC classification number: F01D25/186 ,  F01D11/02 ,  F01D25/166 ,  F01D25/183 ,  F05D2240/61 ,  F16H57/0426 ,  F16J15/164 ,  F16J15/42 ,  F16L27/087

Abstract: A transfer bearing assembly is configured to allow a flow of a fluid from an inlet tube to a channel defined by a rotating shaft. The transfer bearing assembly includes a body having an axially forward side and an axially aft side and a first wing having an axially aft end coupled to the axially forward side and an axially forward end. The transfer bearing assembly also includes a first side plate having a radially outward end coupled to the axially forward end of the first wing and a radially inward end.

公开(公告)号：US20170342858A1

公开(公告)日：2017-11-30

申请号：US15664682

申请日：2017-07-31

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/28 ,  F02C7/36 ,  F04D29/32 ,  F04D29/056 ,  F04D29/053 ,  F04D19/02 ,  F02K3/06 ,  F04D25/04 ,  F02C7/32

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/16 ,  F01D25/28 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/045 ,  F04D29/053 ,  F04D29/056 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671 ,  Y10T29/49321

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a 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 transverse stiffness, at least one journal bearing defining a journal bearing transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness and the journal bearing transverse stiffness is less than or equal to the gear mesh transverse stiffness.

公开(公告)号：US20170298757A1

公开(公告)日：2017-10-19

申请号：US15638954

申请日：2017-06-30

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 ,  F04D19/00 ,  F04D29/053 ,  F01D5/06 ,  F04D25/04 ,  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 according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and a gear system is 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 to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. At least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.