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    Aircraft gas turbine engine blade tip clearance control
    1.
    发明公开
    Aircraft gas turbine engine blade tip clearance control 审中-公开
    Schaufelspitzen-Abstandssteuerungfüreinen Flugzeuggasturbenenotors

    公开(公告)号：EP2025878A2

    公开(公告)日：2009-02-18

    申请号：EP08161497.6

    申请日：2008-07-30

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Hershey, John Erik ,  Osborn, Brock Estel ,  Gardner, Donald Lee ,  Ruiz, Rafael Jose ,  Herron, William Lee

    IPC分类号： F01D11/02 ,  F01D11/20

    CPC分类号： F01D11/24 ,  F02C9/00 ,  F02C9/26 ,  F02C9/48 ,  F05D2270/305 ,  F05D2270/44 ,  F05D2270/70

    摘要： A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

    摘要翻译： 一种方法和系统预计在改变发动机转速的发动机命令之前和之前调整旋转的飞机燃气涡轮发动机叶片尖端和周围的护罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调节顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞行器机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定什么时候开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或在其他飞行器上的其它喷气发动机的操作经验和/或操作经验。

    Seal assembly
    5.
    发明公开
    Seal assembly 审中-公开
    密封组件

    公开(公告)号：EP2020542A1

    公开(公告)日：2009-02-04

    申请号：EP08161286.3

    申请日：2008-07-28

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Varanasi, Kripa ,  Albers, Joseph ,  Herron, William Lee ,  Crudgington, Peter ,  Khandeparker, Mahesh ,  Ippili, Sai Raju ,  Anga, Prathap

    IPC分类号： F16J15/44 ,  F01D11/04

    CPC分类号： F16J15/164 ,  F01D11/005 ,  F01D11/04 ,  F01D25/246 ,  F16J15/445 ,  F16J15/4476

    摘要： A seal assembly (100) comprising a first movable stator member (110) movable between a sealing position and a non-sealing position, a second fixed stator member (102), the first stator member (110) being movable relative to the second stator member (102), the seal assembly (100) further comprising at least one flexure member (150) coupled to the second stator member (102), and at least one biasing member (151) coupled between the at least one flexure (150) and the movable stator (110) for biasing the movable stator (110) to a non-sealing position.

    摘要翻译： 1。一种密封组件（100），包括可在密封位置和非密封位置之间移动的第一可动定子构件（110），第二固定定子构件（102），第一定子构件（110）可相对于第二定子 所述密封组件还包括联接到所述第二定子构件的至少一个挠曲构件以及联接在所述至少一个挠曲件与所述第二定子构件之间的至少一个偏压构件， 和用于将可动定子（110）偏压到非密封位置的可动定子（110）。

    Sealing assembly for gas turbine engines
    6.
    发明公开
    Sealing assembly for gas turbine engines 审中-公开
    DichtungsanordnungfürGasturbinen

    公开(公告)号：EP1852573A2

    公开(公告)日：2007-11-07

    申请号：EP07107277.1

    申请日：2007-05-01

    申请人： The General Electric Company

    发明人： Glynn, Christopher Charles ,  Herron, William Lee ,  Albers, Joseph C.

    IPC分类号： F01D11/04 ,  F01D25/18 ,  F16J15/16

    CPC分类号： F01D11/04 ,  F01D25/183

    摘要： A seal assembly (100) for a gas turbine engine (10) including a stationary stator member (102) and a rotating member (104). The seal assembly includes a primary seal assembly (106), and a secondary seal assembly (108), the primary seal assembly including a moveable stator member (110) including at least one keyed slot (118), and at least one biasing member (114) including at least one key (116) slidably coupled within the at least one keyed slot to facilitate aligning the primary seal assembly and the secondary seal assembly with respect to the gas turbine engine.

    摘要翻译： 一种用于燃气涡轮发动机（10）的密封组件（100），包括固定定子构件（102）和旋转构件（104）。 密封组件包括主密封组件（106）和次级密封组件（108），主密封组件包括可移动的定子构件（110），其包括至少一个键槽（118）和至少一个偏置构件 114）包括可滑动地联接在所述至少一个键槽中的至少一个键（116），以便于相对于所述燃气涡轮发动机对准所述主密封组件和所述次密封组件。

    Method for controlling blade tip clearance in a gas turbine
    10.
    发明公开
    Method for controlling blade tip clearance in a gas turbine 有权
    哥伦布汽油公司的Verfahren zur Regelung des Schaufelspitzenspiels

    公开(公告)号：EP1860281A2

    公开(公告)日：2007-11-28

    申请号：EP07108972.6

    申请日：2007-05-25

    申请人： General Electric Company

    发明人： Herron, William Lee ,  Wiseman, Matthew William ,  Vishnauski, Jon Michael ,  Krupp, Brian Edward ,  Maruscik, Ronald George

    IPC分类号： F01D11/24

    CPC分类号： F01D11/24 ,  F05D2260/80 ,  F05D2270/44 ,  Y02T50/672

    摘要： A method to compensate for blade tip clearance deterioration between rotating blade tips (82) and a surrounding shroud (72) in an aircraft gas turbine engine (10) includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air (36) to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takcoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

    摘要翻译： 补偿在飞行器燃气涡轮发动机（10）中的旋转叶片尖端（82）和周围护罩（72）之间的叶片顶端间隙变差的方法包括基于至少一个或多个移动平均值来确定一个或多个变量， 更多的发动机操作参数分别在固定数量的操作发动机飞行循环中平均，并且基于一个或多个变量来调节热控制空气（36）的流量以抵消叶片顶端间隙恶化。 发动机运行参数可以包括发动机循环的运行次数，起飞和巡航废气温度裕度，巡航涡轮机效率，起飞和巡航最大涡轮机速度，巡航燃料流量。 变量的一些或全部可能分别是发动机运行参数的移动平均值和相应的基线之间的差异，或者变量都可以是移动平均线。 流量可以逐渐调整。