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公开(公告)号：WO2014133644A2
公开(公告)日：2014-09-04
申请号：PCT/US2013/075273
申请日：2013-12-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MCCAFFREY, Michael, G. , ROUSE, Brandon, T. , ALMY, Thomas , GARCIA, Igor, S. , FARRIS, John, R. , BORJA, Mark
CPC classification number: F01D11/18 , F05D2240/11 , F05D2300/50212 , Y02T50/671
Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75 -175% of the second coefficient of thermal expansion.
Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封系统包括由具有第一热膨胀系数的第一材料制成的多个环形载体。 多个密封段分别承载在多个环形载体上。 在多个环形载体中承载环构件。 环构件由与组成中的第一材料不同的第二材料制成。 第二材料具有第二热膨胀系数，使得第一热膨胀系数为第二热膨胀系数的75-175％。
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公开(公告)号：WO2014133483A1
公开(公告)日：2014-09-04
申请号：PCT/US2013/027773
申请日：2013-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： McCAFFREY, Michael G. , GARCIA, Igor, S. , FARRIS, John, R. , PELLETIER, Brian, R. , ALMY, Thomas , ROUSE, Brandon, T. , BORJA, Mark
IPC: F01D11/08
CPC classification number: F01D11/08 , B23P19/00 , F01D9/04 , F01D11/20 , F01D25/246 , Y10T29/49325
Abstract: A clearance control ring (48) having at least two segments (58) is disclosed. Each of the segments (58) interlock with adjacent segments (58) to form a full hoop clearance control ring (48). Separate carriers (54) and seals (50) or one- piece carriers (54) and seals (50) may be mounted on the clearance control ring (48). The segmented structure of the clearance control ring (48) allows for simpler assembly with segmented cases (52) for gas turbine engines (20) than prior art one- piece clearance control rings. The segmented structure also may be used with one- piece pre-assembled and multi-stage rotors (56).
Abstract translation: 公开了具有至少两个段（58）的间隙控制环（48）。 每个段（58）与相邻段（58）互锁以形成完整的环空间隙控制环（48）。 分离的载体（54）和密封件（50）或一体式载体（54）和密封件（50）可以安装在间隙控制环（48）上。 间隙控制环（48）的分段结构允许与现有技术的单件间隙控制环相比，用于燃气涡轮发动机（20）的分段壳体（52）更简单地组装。 分段结构还可以与单件预组装和多级转子（56）一起使用。
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公开(公告)号：WO2014189590A2
公开(公告)日：2014-11-27
申请号：PCT/US2014/020468
申请日：2014-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MCCAFFREY, Michael G. , BORJA, Mark , ROUSE, Brandon T. , FARRIS, John R. , PELLETIER, Brian R. , ALMY, Thomas , GARCIA, Igor S.
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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Patent Agency Ranking
公开(公告)号：WO2015023321A3
公开(公告)日：2015-02-19
申请号：PCT/US2014/033149
申请日：2014-04-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MCCAFFREY, Michael, G. , ROUSE, Brandon, T. , BORJA, Mark , GARCIA, Igor, S. , FARRIS, John, R. , ALMY, Thomas , PELLETIER, Brian, R.
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：EP2964903B1
公开(公告)日：2019-07-03
申请号：EP14801010.1
申请日：2014-03-05
Applicant: United Technologies Corporation
Inventor： MCCAFFREY, Michael G. , BORJA, Mark , ROUSE, Brandon T. , FARRIS, John R. , PELLETIER, Brian R. , ALMY, Thomas , GARCIA, Igor S.
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公开(公告)号：EP2964903A2
公开(公告)日：2016-01-13
申请号：EP14801010.1
申请日：2014-03-05
Applicant: United Technologies Corporation
Inventor： MCCAFFREY, Michael G. , BORJA, Mark , ROUSE, Brandon T. , FARRIS, John R. , PELLETIER, Brian R. , ALMY, Thomas , GARCIA, Igor S.
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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公开(公告)号：EP2938840B1
公开(公告)日：2019-04-10
申请号：EP13876286.9
申请日：2013-12-16
Applicant: United Technologies Corporation
Inventor： MCCAFFREY, Michael, G. , ROUSE, Brandon, T. , ALMY, Thomas , GARCIA, Igor, S. , FARRIS, John, R. , BORJA, Mark
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公开(公告)号：EP2938840A2
公开(公告)日：2015-11-04
申请号：EP13876286.9
申请日：2013-12-16
Applicant: United Technologies Corporation
Inventor： MCCAFFREY, Michael, G. , ROUSE, Brandon, T. , ALMY, Thomas , GARCIA, Igor, S. , FARRIS, John, R. , BORJA, Mark
CPC classification number: F01D11/18 , F05D2240/11 , F05D2300/50212 , Y02T50/671
Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75 -175% of the second coefficient of thermal expansion.
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