公开(公告)号：US10533575B2

公开(公告)日：2020-01-14

申请号：US15696978

申请日：2017-09-06

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  James Glaspey

IPC: F01D11/12 ,  F04D29/38 ,  F04D29/52 ,  F02C3/04

Abstract: Disclosed is a fan blade for a gas turbine engine, the fan blade having: an airfoil having a leading edge, a trailing edge, a tip, and a frangible strip connected to the blade tip and extending outwardly therefrom, the frangible strip being less resistant to plastic deformation than the fan blade tip.

公开(公告)号：US10161264B2

公开(公告)日：2018-12-25

申请号：US15495483

申请日：2017-04-24

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  Thomas Gresham ,  Michael D. Greenberg

IPC: F01D25/16 ,  F16C17/02 ,  F16C27/02 ,  F16C35/02 ,  F02C7/06

Abstract: A bearing damper assembly for a bearing compartment of a gas turbine engine includes a squirrel cage, a bearing support, an outer sleeve, and an inner sleeve. The bearing support is disposed radially outward from a portion of the squirrel cage. The outer sleeve extends axially from the bearing support. The inner sleeve is attached to the squirrel cage and is disposed radially inward from the outer sleeve. An outward surface of the inner sleeve has a first contoured portion having a first axially extending contour and an inner surface of the outer sleeve has a second contoured portion having a second axially extending contour. The outward surface of the inner sleeve and the inner surface of the outer sleeve define a gap extending between the first contoured portion and the second contoured portion. The gap forms a fluid damper.

公开(公告)号：US20180306061A1

公开(公告)日：2018-10-25

申请号：US15495483

申请日：2017-04-24

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  Thomas Gresham ,  Michael D. Greenberg

IPC: F01D25/16 ,  F02C7/06 ,  F16C17/02 ,  F16C27/02 ,  F16C35/02

CPC classification number: F01D25/164 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/54 ,  F16C17/02 ,  F16C27/02 ,  F16C27/045 ,  F16C35/02 ,  F16C2360/23

Abstract: A bearing damper assembly for a bearing compartment of a gas turbine engine includes a squirrel cage, a bearing support, an outer sleeve, and an inner sleeve. The bearing support is disposed radially outward from a portion of the squirrel cage. The outer sleeve extends axially from the bearing support. The inner sleeve is attached to the squirrel cage and is disposed radially inward from the outer sleeve. An outward surface of the inner sleeve has a first contoured portion having a first axially extending contour and an inner surface of the outer sleeve has a second contoured portion having a second axially extending contour. The outward surface of the inner sleeve and the inner surface of the outer sleeve define a gap extending between the first contoured portion and the second contoured portion. The gap forms a fluid damper.

公开(公告)号：US20180119563A1

公开(公告)日：2018-05-03

申请号：US15856421

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 drivingly 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 said ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.

公开(公告)号：US20180094540A1

公开(公告)日：2018-04-05

申请号：US15788373

申请日：2017-10-19

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/32 ,  F02C7/36 ,  F04D29/056 ,  F04D19/02 ,  F02K3/06 ,  F04D29/053 ,  F04D29/32 ,  F01D5/06 ,  F01D9/02 ,  F04D25/04 ,  F01D25/28 ,  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 includes a fan that has fan blades. A fan shaft is drivingly connected to the fan. A frame supports the fan shaft and defines a frame 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 frame lateral stiffness.

公开(公告)号：US20170335718A1

公开(公告)日：2017-11-23

申请号：US15606494

申请日：2017-05-26

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: F02C7/36 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/16 ,  F01D25/164 ,  F01D25/28 ,  F02C7/32 ,  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 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：US20170306855A1

公开(公告)日：2017-10-26

申请号：US15440412

申请日：2017-02-23

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C7/36 ,  F02C7/20 ,  F01D15/12 ,  F02K3/06 ,  F02C3/107

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：US20170260876A1

公开(公告)日：2017-09-14

申请号：US15606776

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 a gear system connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A flexible support supports the gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 8% of the gear mesh transverse stiffness.

公开(公告)号：US20170218849A1

公开(公告)日：2017-08-03

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: F02C7/36 ,  F01D15/12 ,  F01D5/06 ,  F01D9/04 ,  F04D25/04 ,  F04D29/32

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：US20170175583A1

公开(公告)日：2017-06-22

申请号：US15452232

申请日：2017-03-07

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

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

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 supporting the fan shaft. A gear system connected to the fan shaft includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness, and a gear mesh transverse stiffness. The gear system also includes a reduction ratio greater than 2.3. A gear system input to the gear system defines a gear system input lateral stiffness. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness and the gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness.