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1.发明申请RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER 审中-公开具有轴向反应构件的壳体支撑结构的径向位置控制公开(公告)号：US20160053624A1
公开(公告)日：2016-02-25
申请号：US14781263
申请日：2014-04-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Brandon T. Rouse , Mark Borja , Igor S. Garcia , John R. Farris , Thomas Almy , Brian R. Pelletier
CPC classification number: F01D11/08 , F01D9/04 , F01D11/12 , F01D11/14 , F01D11/20 , F01D11/22 , F01D11/24 , F01D25/24 , Y02T50/672
Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.
Abstract translation: 用于燃气涡轮发动机级的径向位置控制组件包括壳体结构。 支撑结构由壳体结构可操作地支撑。 支撑环可操作地支撑所支撑的结构。 支撑结构和支撑环具有不同的热膨胀系数。 密封结构与支撑结构相邻。 基于相邻的支撑结构之间的周向间隙，并且基于支撑环和支撑结构之间的径向间隙，支撑环在热瞬变期间的间隙处相对于密封结构保持支撑结构。 销支撑相对于壳体结构的支撑结构，并且被配置为将支撑环与支撑结构上的负载隔离开。
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公开(公告)号：US10280782B2
公开(公告)日：2019-05-07
申请号：US14759317
申请日：2013-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Igor S. Garcia , John R. Farris , Brian R. Pelletier , Thomas Almy , Brandon T. Rouse , Mark Borja
Abstract: A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.
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Patent Agency Ranking
3.发明申请公开(公告)号：US20160341075A1
公开(公告)日：2016-11-24
申请号：US15106615
申请日：2014-08-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shu Liu , Robert Russell Mayer , Paul W. Palmer , Peter Balawajder , Igor S. Garcia , David C. Pimenta , Stephanie Ernst , Fernando K. Grant , Eric Baker , Andrew S. Miller
CPC classification number: F01D25/26 , F01D21/045 , F01D25/24 , F02C3/04 , F02K3/06 , F04D29/522 , F04D29/526 , F05D2220/32 , F05D2250/283 , F05D2250/29 , F05D2300/506 , F23R3/002
Abstract: A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments.
Abstract translation: 燃气涡轮发动机包括具有芯壳的芯组件，所述芯壳具有用于容纳释放的压缩机和涡轮叶片和叶片碎片的容纳部分。 容纳部分包括第一和第二容纳层，并且容纳部分被配置为具有穿过第一和第二容纳层的非线性能量消耗速率，从而改善叶片和叶片碎片的收容。
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公开(公告)号：US10053999B2
公开(公告)日：2018-08-21
申请号：US14781263
申请日：2014-04-07
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Brandon T. Rouse , Mark Borja , Igor S. Garcia , John R. Farris , Thomas Almy , Brian R. Pelletier
CPC classification number: F01D11/08 , F01D9/04 , F01D11/12 , F01D11/14 , F01D11/20 , F01D11/22 , F01D11/24 , F01D25/24 , Y02T50/672
Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.
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公开(公告)号：US09957830B2
公开(公告)日：2018-05-01
申请号：US14765117
申请日：2014-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Mark Borja , Brandon T. Rouse , John R. Farris , Brian R. Pelletier , Thomas Almy , Igor S. Garcia
CPC classification number: F01D11/18 , F01D5/02 , F01D11/22 , F01D11/24 , F01D25/24 , F05D2220/32 , F05D2240/55 , F05D2270/52 , F05D2270/62
Abstract: A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater.
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6.发明申请公开(公告)号：US20160341070A1
公开(公告)日：2016-11-24
申请号：US15106566
申请日：2014-08-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Igor S. Garcia , Shu Liu , Robert Russell Mayer , Eric Baker , Stephanie Ernst , Fernando K. Grant , Andrew S. Miller , Peter Balawajder , Paul W. Palmer
Abstract: A gas turbine engine includes a containment ring to contain liberated compressor and turbine blades and blade fragments within a core assembly. The combination of a containment gap between the core case and the containment ring and a containment layer disposed in the gap helps dissipate the energy generated by loose body impacts on the core assembly. The containment layer deforms, deflects, and/or redirects the impact energy acting in a radial direction, thereby to improve containment.
Abstract translation: 燃气涡轮发动机包括容纳环，以容纳释放的压缩机和涡轮叶片以及芯组件内的叶片碎片。 芯壳与容纳环之间的容纳间隙和设置在间隙中的容纳层的组合有助于消散由芯体组件上的松动的身体撞击产生的能量。 容纳层使沿径向作用的冲击能量变形，偏转和/或重定向，从而改善容纳。
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公开(公告)号：US20150369076A1
公开(公告)日：2015-12-24
申请号：US14765117
申请日：2014-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Mark Borja , Brandon T. Rouse , John R. Farris , Brian R. Pelletier , Thomas Almy , Igor S. Garcia
CPC classification number: F01D11/18 , F01D5/02 , F01D11/22 , F01D11/24 , F01D25/24 , F05D2220/32 , F05D2240/55 , F05D2270/52 , F05D2270/62
Abstract: A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater.
Abstract translation: 控制环围绕中心轴线周向延伸。 多个周向间隔的载体部分具有容纳控制环的空腔。 载体部分之间有圆周间隙。 叶片外部空气密封件安装在控制环径向向内的托架部分上。 当通过电加热器加热时，控制环将承载部分保持在径向向外扩展的位置。
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