公开(公告)号：US09771871B2

公开(公告)日：2017-09-26

申请号：US14792927

申请日：2015-07-07

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  Drew W. Lancaster

IPC: F04D29/043 ,  F02C7/36 ,  F01D5/02 ,  F01D21/04 ,  F02C3/04

CPC classification number: F02C7/36 ,  F01D5/02 ,  F01D21/045 ,  F02C3/04 ,  F04D29/043 ,  F04D29/053 ,  F05D2220/36

Abstract: A fan shaft includes a first end, a second end, and an axis, the fan shaft and configured to be coupled to a gear assembly of a gas turbine engine at the first end and to a fan more proximal to the second end than the first end such that in response to being coupled, the fan shaft can transfer torque from the gear assembly to the fan. At least one axial portion of the fan shaft satisfies the relationship 0.55 ≤ T * C J * τ ≤ 0.95 , where T represents peak torque during fan blade off, C represents a distance from a centerline of the gas turbine engine to an outer fiber of the fan shaft, J represents a polar moment of inertia of the fan shaft, and τ represents yield stress in shear of the fan shaft.

公开(公告)号：US20170218850A1

公开(公告)日：2017-08-03

申请号：US15485563

申请日：2017-04-12

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 ,  F04D25/04 ,  F01D5/06 ,  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 defined 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 between 0.5 and 1.5.

公开(公告)号：US20170218789A1

公开(公告)日：2017-08-03

申请号：US15485512

申请日：2017-04-12

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 ,  F01D5/06 ,  F04D19/00 ,  F04D25/04

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 defined 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 between 0.5 and 1.5.

公开(公告)号：US09631558B2

公开(公告)日：2017-04-25

申请号：US13908177

申请日：2013-06-03

Applicant: UNITED TECHNOLOGIES CORPORATION

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

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

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 flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

公开(公告)号：US20160053635A1

公开(公告)日：2016-02-25

申请号：US14859381

申请日：2015-09-21

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F01D15/12 ,  F01D25/28

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 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.

Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括构造成驱动风扇的风扇轴，构造成支撑风扇轴的至少一部分的支撑件，支撑件限定支撑横向刚度和 支撑横向刚度，耦合到所述风扇轴的齿轮系统以及被配置为至少部分地支撑所述齿轮系统的柔性支撑件。 柔性支撑件相对于支撑横向刚度和相对于支撑横向刚度的柔性支撑横向刚度限定了柔性支撑横向刚度。 该输入定义了相对于支撑横向刚度的输入横向刚度和相对于支撑横向刚度的输入侧向刚度。

公开(公告)号：US08770922B2

公开(公告)日：2014-07-08

申请号：US14160601

申请日：2014-01-22

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/28 ,  F02C7/36

CPC classification number: F02C7/36 ,  F01D25/164 ,  F05D2260/96 ,  Y02T50/671

Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.

Abstract translation: 燃气涡轮发动机包括风扇轴和支撑风扇轴的支撑件。 支撑件限定支撑横向和支撑横向刚度中的至少一个。 齿轮系驱动风扇轴。 柔性支撑件至少部分地支撑齿轮系统，并且相对于支撑横向和支撑横向刚度中的至少一个限定柔性支撑横向和柔性支撑横向刚度中的至少一个。 相对于支撑横向和支撑横向刚度中的至少一个，齿轮系统的输入限定了输入横向刚度和输入横向刚度中的至少一个。 还公开了一种设计燃气涡轮发动机的方法。

公开(公告)号：US08756908B2

公开(公告)日：2014-06-24

申请号：US14034720

申请日：2013-09-24

Applicant: United Technologies Corporation

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

IPC: F02C7/06

CPC classification number: F02C7/06 ,  F01D25/18 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  Y02T50/671

Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.

Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括能量消除等于输入到齿轮系统中的能量的小于约2％的能量。

公开(公告)号：US11415064B2

公开(公告)日：2022-08-16

申请号：US16689690

申请日：2019-11-20

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  William G. Sheridan

IPC: F02C7/36 ,  F16H57/00 ,  F16H57/08

Abstract: A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a geared architecture. A flexible support supports the geared architecture relative to an engine static structure. A deflection limiter includes at least one of an axially extending branch or a radially extending branch. A flexible output shaft is in driving engagement with the fan section and driven by the geared architecture. A speed change mechanism for a gas turbine engine is also disclosed.

公开(公告)号：US11215122B2

公开(公告)日：2022-01-04

申请号：US16689656

申请日：2019-11-20

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Jason Husband

IPC: F02C7/36 ,  F02C7/06

Abstract: A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a planetary gear system. The planetary gear system includes a plurality of planet gears surrounding a sun gear. A carrier supports the plurality of planet gears and includes a first carrier bearing flange. A ring gear surrounds the plurality of planet gears and includes a ring gear bearing flange. At least one ring gear carrier bearing engages the carrier bearing flange and the ring gear bearing flange. A speed change mechanism for a gas turbine is also disclosed.

公开(公告)号：US11092020B2

公开(公告)日：2021-08-17

申请号：US16163641

申请日：2018-10-18

Applicant: United Technologies Corporation

Inventor： Jason Husband ,  James Glaspey ,  Aaron John Pepin

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28 ,  F01D11/00 ,  F01D5/02

Abstract: A rotor assembly for a gas turbine engine includes, among other things, a rotatable hub that has a metallic main body that extends along a longitudinal axis, and that has an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels along the longitudinal axis. Each of the annular channels receives a composite reinforcement member that extends about the outer periphery of the hub.