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公开(公告)号：US20170276010A1
公开(公告)日：2017-09-28
申请号：US15606522
申请日：2017-05-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
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 supported by a fan shaft support defining a fan shaft support lateral and transverse stiffness. A gear system connected to the fan shaft including a ring gear defining a ring gear lateral and transverse stiffness, a gear mesh defining a gear mesh lateral and transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral and transverse stiffness is less than 12% of a respective one of the gear mesh lateral and transverse stiffness. A flexible support supports the gear system and defines a flexible support lateral and transverse stiffness. At least one of the flexible support lateral and transverse stiffness is less than 11% of a respective one of the fan shaft support lateral and transverse stiffness.
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公开(公告)号：US20170248191A1
公开(公告)日：2017-08-31
申请号：US15053803
申请日：2016-02-25
Applicant: United Technologies Corporation
Inventor： Jason Husband , John Zhiqiang Wang
IPC: F16F15/023 , F16C19/52 , F01D25/16 , F16F9/10
CPC classification number: F16F15/023 , B22F3/1055 , B22F5/009 , B22F2998/10 , B22F2999/00 , B33Y10/00 , B33Y80/00 , F01D25/125 , F01D25/164 , F05D2250/182 , F05D2250/184 , F05D2250/294 , F16C19/06 , F16C19/527 , F16C27/045 , F16C2220/00 , F16C2360/23 , F16F9/10 , F16F15/0237 , Y02T50/675 , B22F5/106 , B22F7/06
Abstract: A damper system may include an inner damper having a first annular geometry and a textured surface. An outer damper may also have an annular geometry and be disposed about the inner damper. The outer damper may have a textured surface. The textured surfaces of the inner damper and outer damper may define a cavity that is configured to contain a viscous fluid.
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公开(公告)号：US20170226936A1
公开(公告)日：2017-08-10
申请号：US15485481
申请日：2017-04-12
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
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. 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.
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14.发明授权公开(公告)号：US09410608B2
公开(公告)日：2016-08-09
申请号：US13938466
申请日：2013-07-10
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
IPC: F16H57/028 , F02C7/36 , F01D25/16
CPC classification number: F16H57/028 , F01D25/164 , F02C7/36 , F02K3/06 , F04D25/028 , F04D29/053 , F04D29/056 , F05D2220/323 , F05D2260/40311 , F05D2300/501 , F16H1/28
Abstract: A geared architecture for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan shaft, a frame which supports the fan shaft, the frame defines a frame stiffness and a plurality of gears which drives the fan shaft. A flexible support defines a flexible support stiffness that is less than the frame stiffness. The plurality of gears are supported by at least one of a carrier and the flexible support and an input coupling to the plurality of gears, the input coupling defines an input coupling stiffness with respect to the frame stiffness.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的齿轮架构包括风扇轴，支撑风扇轴的框架，框架限定框架刚度和驱动风扇的多个齿轮 轴。 柔性支撑件限定了小于框架刚度的柔性支撑刚度。 多个齿轮由载体和柔性支撑件中的至少一个支撑，以及与多个齿轮的输入联接，输入联接器限定相对于框架刚度的输入联接刚度。
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15.发明申请公开(公告)号：US20160017746A1
公开(公告)日：2016-01-21
申请号：US14773924
申请日：2013-12-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Husband , Drew W. Lancaster
CPC classification number: F01D21/006 , F01D5/02 , F01D15/12 , F01D21/045 , F05D2220/323 , F05D2220/36 , F05D2260/40311 , F05D2260/902 , Y02T50/671
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.
Abstract translation: 一种涡轮风扇发动机，其包括风扇部分，所述风扇部分包括可围绕轴线旋转的多个风扇叶片，包括多个压缩机叶片的压缩机，包括多个涡轮机叶片的涡轮机以及由所述涡轮机驱动的齿轮架构， 公开了与涡轮机不同的速度和方向。 接近压缩机叶片，涡轮机叶片和风扇叶片中的至少一个的摩擦带在接合时减慢旋转。 当处于非接合状态下遇到的扭矩的2至6倍的接合状态时，摩擦带产生相反的转矩。
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Patent Agency Ranking
16.发明申请公开(公告)号：US20150345398A1
公开(公告)日：2015-12-03
申请号：US14604811
申请日：2015-01-26
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
CPC classification number: F01D25/164 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/28 , F02C7/32 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/053 , F04D29/056 , F04D29/325 , F05D2220/32 , F05D2240/60 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y10T29/49321
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。
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公开(公告)号：US11359500B2
公开(公告)日：2022-06-14
申请号：US16163654
申请日：2018-10-18
Applicant: United Technologies Corporation
Inventor： Jason Husband , James Glaspey
Abstract: A platform for a gas turbine engine according to an example of the present disclosure includes, among other things, a platform body that extends in a circumferential direction between first and second sidewalls to define a gas path surface, and opposed rows of flexible retention tabs that extend from the platform body and are dimensioned to wedge the platform between adjacent airfoils.
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公开(公告)号：US11009036B2
公开(公告)日：2021-05-18
申请号：US16117500
申请日：2018-08-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Husband , James Glaspey
IPC: F04D29/38 , F01D5/14 , F01D5/18 , F04D19/00 , F04D29/32 , F04D29/64 , F04D29/02 , F01D5/12 , B23P15/04
Abstract: A blade for use in a gas turbine engine is disclosed. In various embodiments, the blade includes a pressure side sheath and a suction side sheath secured to the pressure side sheath. The pressure side sheath and the suction side sheath are configured to form a continuous sheath that wraps around an interior section of the blade.
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公开(公告)号：US10753281B2
公开(公告)日：2020-08-25
申请号：US15819011
申请日：2017-11-21
Applicant: United Technologies Corporation
Inventor： Kaliya Balamurugan , Jason Husband
Abstract: A multi-shaft assembly includes an inner shaft and an outer shaft coaxially aligned with the inner shaft to establish a shared axis of rotation. The multi-shaft assembly also includes an ablatable shaft feature with a lubricant surface coating on an interior surface of the outer shaft and an ablatable metallic alloy layer overlaying a portion of the lubricant surface coating with a radial air gap formed between the ablatable metallic alloy layer and an exterior surface of the inner shaft.
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公开(公告)号：US20200072235A1
公开(公告)日：2020-03-05
申请号：US16117500
申请日：2018-08-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Husband , James Glaspey
Abstract: A blade for use in a gas turbine engine is disclosed. In various embodiments, the blade includes a pressure side sheath and a suction side sheath secured to the pressure side sheath. The pressure side sheath and the suction side sheath are configured to form a continuous sheath that wraps around an interior section of the blade.
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