公开(公告)号：US10584714B2

公开(公告)日：2020-03-10

申请号：US15812331

申请日：2017-11-14

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  James Glaspey

IPC: F01D5/22 ,  F04D29/32 ,  F02K3/06 ,  F04D19/00 ,  F04D29/66

Abstract: A fan of a gas turbine engine is provided. The fan having: a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end and a tip portion that is secured to a shroud that circumscribes the plurality of fan blades.

公开(公告)号：US20200025032A1

公开(公告)日：2020-01-23

申请号：US16298319

申请日：2019-03-11

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

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

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 defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.

公开(公告)号：US10352194B2

公开(公告)日：2019-07-16

申请号：US15690554

申请日：2017-08-30

Applicant: United Technologies Corporation

Inventor： Philip Andrew Varney ,  Jason Husband

IPC: F16C19/06 ,  F16C33/10 ,  F16C27/00 ,  F16C33/66 ,  F01D25/16 ,  F01D25/18 ,  F01D11/00 ,  F16F15/023 ,  F16C27/04

Abstract: A bearing assembly includes a case, a bearing spring positioned inside the case, a first seal positioned between the case and the bearing spring, and a second seal. The a second seal is positioned between the case and the bearing spring and is spaced apart from the first seal, wherein the second seal is an adjustable seal that is movable between a closed position and an opened position to inhibit or allow, respectively, a fluid to flow from a cavity that is defined by the case, the bearing spring, the first seal and the second seal.

公开(公告)号：US20190145423A1

公开(公告)日：2019-05-16

申请号：US15812331

申请日：2017-11-14

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  James Glaspey

IPC: F04D29/32 ,  F02K3/06 ,  F04D19/00 ,  F04D29/66

Abstract: A fan of a gas turbine engine is provided. The fan having: a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end and a tip portion that is secured to a shroud that circumscribes the plurality of fan blades.

公开(公告)号：US20190063452A1

公开(公告)日：2019-02-28

申请号：US15689946

申请日：2017-08-29

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  James Glaspey

IPC: F04D29/32 ,  F04D29/34 ,  F01D21/04

Abstract: A conical hub for a fan of a gas turbine engine is provided. The conical hub having: a plurality of attachment features located on an outer circumferential surface of the conical hub, wherein at least some of the plurality attachment features are axially aligned with each other and at least some of the plurality of attachment features are off set from each other, and wherein each of the plurality of attachment features have an opening configured to receive a portion of a pin; and the outer circumferential surface of the conical hub increases in diameter with respect to an axis of the conical hub in a forward to aft direction of the conical hub.

公开(公告)号：US20190063261A1

公开(公告)日：2019-02-28

申请号：US15690554

申请日：2017-08-30

Applicant: United Technologies Corporation

Inventor： Philip Andrew Varney ,  Jason Husband

IPC: F01D25/16 ,  F01D11/00 ,  F16C19/06 ,  F16C27/00

CPC classification number: F01D25/164 ,  F01D11/003 ,  F01D25/183 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2260/98 ,  F16C19/06 ,  F16C27/00 ,  F16C27/045 ,  F16C33/104 ,  F16C33/6659 ,  F16C2360/23 ,  F16F15/0237

Abstract: A bearing assembly includes a case, a bearing spring positioned inside the case, a first seal positioned between the case and the bearing spring, and a second seal. The a second seal is positioned between the case and the bearing spring and is spaced apart from the first seal, wherein the second seal is an adjustable seal that is movable between a closed position and an opened position to inhibit or allow, respectively, a fluid to flow from a cavity that is defined by the case, the bearing spring, the first seal and the second seal.

公开(公告)号：US20180094532A1

公开(公告)日：2018-04-05

申请号：US15816512

申请日：2017-11-17

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 includes a fan shaft that has fan blades. A fan shaft is drivingly connected to the fan. A fan shaft support supports the fan shaft and defines a fan shaft support lateral stiffness. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation and includes a flexible support that defines a flexible support lateral stiffness that is less than 11% of the shaft support lateral stiffness.

公开(公告)号：US20170260875A1

公开(公告)日：2017-09-14

申请号：US15606556

申请日：2017-05-26

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/32 ,  F01D25/28 ,  F02C7/36 ,  F01D15/12

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 defines a fan shaft support transverse stiffness. A gear system connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A flexible support supports said gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.

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：US20170175581A1

公开(公告)日：2017-06-22

申请号：US15451929

申请日：2017-03-07

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

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

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, 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.