公开(公告)号：WO2015023321A2

公开(公告)日：2015-02-19

申请号：PCT/US2014033149

申请日：2014-04-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T ,  BORJA MARK ,  GARCIA IGOR S ,  FARRIS JOHN R ,  ALMY THOMAS ,  PELLETIER BRIAN R

IPC: F01D11/22 ,  F02C7/28

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: 用于燃气轮机发动机级的径向位置控制组件包括壳体结构。 受支持的结构由壳体结构可操作地支撑。 支撑环可操作地支撑被支撑的结构。 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。 支撑环基于相邻支撑结构之间的周向间隙并且基于支撑环与支撑结构之间的径向间隙，在热瞬变期间在间隙处相对于密封结构保持支撑结构。 销相对于壳体结构支撑被支撑的结构，并被配置为将支撑环与被支撑结构上的载荷隔离。

公开(公告)号：WO2014189590A3

公开(公告)日：2015-02-26

申请号：PCT/US2014020468

申请日：2014-03-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  BORJA MARK ,  ROUSE BRANDON T ,  FARRIS JOHN R ,  PELLETIER BRIAN R ,  ALMY THOMAS ,  GARCIA IGOR S

IPC: F01D11/14 ,  F01D11/18 ,  F01D11/20 ,  F01D11/22

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。

公开(公告)号：WO2014133644A3

公开(公告)日：2014-11-27

申请号：PCT/US2013075273

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T ,  ALMY THOMAS ,  GARCIA IGOR S ,  FARRIS JOHN R ,  BORJA MARK

IPC: F01D11/18 ,  F02C7/28 ,  F04D29/08

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载体。 多个密封段分别承载在多个环形托架上。 环形部件被承载在多个环形托架中。 环构件由与构成中的第一材料不同的第二材料构成。 第二材料具有第二热膨胀系数，使得第一热膨胀系数是第二热膨胀系数的75-175％。

公开(公告)号：EP2964903A4

公开(公告)日：2016-12-21

申请号：EP14801010

申请日：2014-03-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  BORJA MARK ,  ROUSE BRANDON T ,  FARRIS JOHN R ,  PELLETIER BRIAN R ,  ALMY THOMAS ,  GARCIA IGOR S

IPC: F01D11/14 ,  F01D5/02 ,  F01D11/18 ,  F01D11/20 ,  F01D11/22 ,  F01D11/24 ,  F01D25/24

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.

公开(公告)号：EP2938840A4

公开(公告)日：2016-05-25

申请号：EP13876286

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T ,  ALMY THOMAS ,  GARCIA IGOR S ,  FARRIS JOHN R ,  BORJA MARK

IPC: F01D11/18 ,  F02C7/28 ,  F04D29/08

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.