公开(公告)号：US10724535B2

公开(公告)日：2020-07-28

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：US20200232342A1

公开(公告)日：2020-07-23

申请号：US16667154

申请日：2019-10-29

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 includes a fan shaft that drives a fan that has fan blades. An outer housing surrounds the fan. A bypass flow path is within the outer housing. A fan shaft support that supports the fan shaft defines a fan shaft support transverse stiffness. A gear system is connected to the fan shaft. The gear system includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support which supports the gear system relative to a static structure defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness. The flexible support transverse stiffness is less than 8% of the gear mesh transverse stiffness.

公开(公告)号：US20200158226A1

公开(公告)日：2020-05-21

申请号：US16747934

申请日：2020-01-21

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F16H57/028 ,  F16H1/28 ,  F04D29/056 ,  F04D29/053 ,  F04D25/02 ,  F02K3/06 ,  F01D25/16 ,  F02C7/36

Abstract: A geared architecture for a gas turbine engine includes a fan shaft driving a fan surrounded by an outer housing. A frame that supports the fan shaft and defines a frame lateral stiffness. A plurality of gears are in driving engagement with the fan shaft. The plurality of gears provide an epicyclic gear system which includes a gear mesh defining a gear mesh lateral stiffness and a ring gear defining a ring gear lateral stiffness. The ring gear lateral stiffness is less than 12% of the gear mesh lateral stiffness. A flexible support supports the epicyclic gear system relative to a static structure and defines a flexible support lateral stiffness and a flexible support transverse stiffness. An input coupling to the plurality of gears defines an input coupling lateral stiffness. The flexible support lateral stiffness and the input coupling lateral stiffness are each less than about 11% of said frame lateral stiffness.

公开(公告)号：US10330017B2

公开(公告)日：2019-06-25

申请号：US14902058

申请日：2014-07-03

Applicant: United Technologies Corporation

Inventor： John R. Otto ,  James B. Coffin ,  Jason Husband

IPC: F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02C3/10 ,  F02C3/107

Abstract: A turbofan engine includes a fan rotatable about an axis and a compressor section including a high pressure compressor and a low pressure compressor. A turbine section includes a high pressure turbine, an intermediate turbine and a fan drive turbine. The high pressure turbine is coupled to drive the high pressure compressor. A fan drive gear system is driven by the fan drive turbine for driving the fan and a compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor.

公开(公告)号：US10301968B2

公开(公告)日：2019-05-28

申请号：US14859381

申请日：2015-09-21

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 configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.

公开(公告)号：US10107134B2

公开(公告)日：2018-10-23

申请号：US14773924

申请日：2013-12-03

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  Drew W. Lancaster

IPC: F01D21/00 ,  F01D21/04 ,  F01D5/02 ,  F01D15/12

Abstract: A turbofan engine including a fan section including a plurality of fan blades rotatable about an axis, a compressor including a plurality of compressor blades, a turbine including a plurality of turbine blades and a geared architecture driven by the turbine for driving the fan section at a speed and direction different than the turbine is disclosed. A rub strip proximate at least one of the compressor blades, the turbine blades and the fan blades slows rotation when engaged. The rub strip generates a torque opposing rotation when in an engaged condition that is between 2 and 6 times a torque encountered in a non-engaged condition.

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：US20180094541A1

公开(公告)日：2018-04-05

申请号：US15788393

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 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F01D5/06 ,  F01D9/02 ,  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 shaft is drivingly connected to a fan having fan blades. A gear system is connected to the fan shaft and driven through an input having a gear reduction ratio of greater than 2.3. A gear system flex mount arrangement accommodates for misalignment of the fan shaft and the input during operation and includes a gear mesh defining a gear mesh transverse stiffness and a ring gear defining a ring gear transverse stiffness that is less than 20% of the gear mesh transverse stiffness. A bypass ratio is greater than ten (10). A fan pressure ratio is less than 1.45 measured across the fan blades alone. A low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1. The low pressure turbine pressure ratio is a ratio of a pressure measured prior to the inlet as related to a pressure at the outlet prior to any exhaust nozzle.

公开(公告)号：US20170298770A1

公开(公告)日：2017-10-19

申请号：US15639188

申请日：2017-06-30

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 ring gear defining a ring gear lateral stiffness, a gear mesh defining a gear mesh lateral stiffness, and a reduction ratio greater than 2.3. A bypass ratio is greater than 10 (10). The ring gear lateral stiffness is less than 12% of the gear mesh lateral stiffness.

公开(公告)号：US20170298768A1

公开(公告)日：2017-10-19

申请号：US15485732

申请日：2017-04-12

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 defining a fan shaft support lateral stiffness and a fan shaft support transverse stiffness and a gear system connected to the fan shaft having a reduction ratio of greater than 2.3. A flexible support supports the gear system and defines a flexible support lateral stiffness and a flexible support transverse stiffness. A low fan pressure ratio of less than 1.45 measured across the fan blades alone. At least one of the flexible support lateral stiffness is less than 11% of the fan shaft support lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.