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公开(公告)号：US10443435B2
公开(公告)日：2019-10-15
申请号：US14969426
申请日：2015-12-15
Applicant: United Technologies Corporation
Inventor： Richard K. Hayford , Michael J. Bruskotter , Ross A. Vandenbosch
Abstract: A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.
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公开(公告)号：US10125636B2
公开(公告)日：2018-11-13
申请号：US15042372
申请日：2016-02-12
Applicant: United Technologies Corporation
Inventor： David P. Dube , Richard K. Hayford
Abstract: A bowed rotor prevention system for a gas turbine engine is provided. The bowed rotor prevention system includes a thermoelectric generator system operable to produce electricity from waste heat of the gas turbine engine. The bowed rotor prevention system also includes a bowed rotor prevention motor operable to drive rotation of turbomachinery of the gas turbine engine using the electricity produced by the thermoelectric generator system.
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公开(公告)号：US20180252165A1
公开(公告)日：2018-09-06
申请号：US15688251
申请日：2017-08-28
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Todd M. LaPierre , Richard K. Hayford
IPC: F02C7/36 , F02C3/107 , F02K3/06 , F16H1/46 , F16H57/025 , F16H57/028
Abstract: A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. The gear housing includes a stationary carrier, wherein the forward and aft planet gears are rotatably mounted to the stationary carrier, and a mount extending radially from the stationary carrier that is connectable to a stationary portion of the turbomachine.
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公开(公告)号：US09745898B2
公开(公告)日：2017-08-29
申请号：US14974994
申请日：2015-12-18
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Todd M. LaPierre , Richard K. Hayford
IPC: F16H57/025 , F02C7/36 , F02K3/06 , F02C3/107 , F16H1/46 , F16H57/028
CPC classification number: F02C7/36 , F02C3/107 , F02K3/06 , F05D2260/40311 , F16H1/46 , F16H57/025 , F16H57/028 , Y02T50/671
Abstract: A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. The gear housing includes a stationary carrier, wherein the forward and aft planet gears are rotatably mounted to the stationary carrier, and a mount extending radially from the stationary carrier that is connectable to a stationary portion of the turbomachine.
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公开(公告)号：US20170239763A1
公开(公告)日：2017-08-24
申请号：US15590934
申请日：2017-05-09
Applicant: United Technologies Corporation
Inventor： Philip R. Belanger , Paul M. Lutjen , Richard K. Hayford
CPC classification number: B23P6/045 , B22D21/005 , B23K35/025 , B23K35/3033 , B23K2101/001 , B23P6/002 , B23P6/005 , C22C19/03 , F01D5/005 , F01D11/08 , F05D2220/32 , F05D2230/80 , F05D2240/11 , F05D2300/123 , F05D2300/177
Abstract: A structural element for repairing a damaged component comprising a shaped cavity configured to receive the damaged component and a repair material, the shaped cavity comprising a material having a first melting point and the repair material comprising a material having a second melting point that is lower than the first melting point. The shaped cavity may comprise a preform for the damaged component. The preform may comprise a mold configured to reconstruct the shape of the damaged component. The repair material may comprise a first material and a second material, the second material having a melting point that is lower than the first material. The repair material may comprise a Nickel-Boron composition. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the damaged component.
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Patent Agency Ranking
公开(公告)号：US20160312644A1
公开(公告)日：2016-10-27
申请号：US15105220
申请日：2014-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Richard K. Hayford , Christopher M. Jarochym
Abstract: An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.
Abstract translation: 用于燃气涡轮发动机的示例性主动间隙控制系统包括致动器和限定被配置为接收致动器的孔的壳体壁部分。 致动器构造成移动空气密封段，并且致动器可通过壳体壁部分的径向外侧插入孔内的安装位置。
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公开(公告)号：US20160237839A1
公开(公告)日：2016-08-18
申请号：US15026709
申请日：2014-09-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark J. Rogers , Carl S. Richardson , Richard K. Hayford , Kenneth E. Carman , Jonathan J. Earl
CPC classification number: F01D11/005 , F01D9/041 , F01D11/001 , F01D11/08 , F01D25/04 , F05D2220/32 , F05D2260/52
Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.
Abstract translation: 叶片密封系统包括具有在其一端具有第一凹部的第一翼型件的第一不可旋转叶片段。 第二不可旋转的叶片段包括第二翼型件，在其一端具有与第一凹口间隔开的第二凹口。 密封件横跨该间隙并在第一袋和第二袋中延伸。 密封构件包括密封元件和至少一个弹簧部分，其构造成将密封构件朝向密封方向正向定位。 还公开了一种用于叶片密封系统的密封件及其相关方法，用于阻止第一袋和第二袋之间的相对运动。
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公开(公告)号：US20160169039A1
公开(公告)日：2016-06-16
申请号：US14969426
申请日：2015-12-15
Applicant: United Technologies Corporation
Inventor： Richard K. Hayford , Michael J. Bruskotter , Ross A. Vandenbosch
CPC classification number: F01D25/12 , F01D9/04 , F01D11/18 , F01D25/24 , F01D25/246 , F05D2260/221 , F05D2260/941
Abstract: A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.
Abstract translation: 用于涡轮机的部件包括限定内径部分和外径部分的环形体，以及限定在环形体的表面中的从内径部分向外径向外直径部分延伸的裂缝引导槽， 外径部向径向内侧朝向内径部。 外径部分可以安装在涡轮机的固定结构上。 内径部分可安装在涡轮叶片上。
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公开(公告)号：US20160097291A1
公开(公告)日：2016-04-07
申请号：US14853202
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Richard K. Hayford , Philip Robert Rioux
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D11/001 , F05D2250/294 , F05D2260/941 , F05D2270/114
Abstract: A stator assembly includes a platform located on a radially inner end of a plurality of vanes that connects a first vane to a second vane. There is a platform groove on a radially inner side of the platform between the first vane and the second vane.
Abstract translation: 定子组件包括位于将第一叶片连接到第二叶片的多个叶片的径向内端上的平台。 在第一叶片和第二叶片之间的平台的径向内侧上具有平台槽。
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公开(公告)号：US11021962B2
公开(公告)日：2021-06-01
申请号：US16108763
申请日：2018-08-22
Applicant: United Technologies Corporation
Inventor： Neil L. Tatman , Nathan K. Galle , Richard K. Hayford
Abstract: A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.
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