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    TIP CLEARANCE CONTROL SYSTEM
    2.
    发明申请
    TIP CLEARANCE CONTROL SYSTEM 审中-公开
    提示间隙控制系统

    公开(公告)号：WO2007086893A2

    公开(公告)日：2007-08-02

    申请号：PCT/US2006/010013

    申请日：2006-03-17

    Applicant: UNITED TECHNOLOGIES CORPORATION ,  KANE, Daniel, E.

    Inventor： KANE, Daniel, E.

    IPC: G06F19/00

    CPC classification number: F01D11/20 ,  F01D11/24 ,  F05D2270/301 ,  F05D2270/702

    Abstract: The invention is a method for controlling blade tip clearance in a turbine engine having a flowpath extending therethrough, and a system for carrying out the method. The method includes acquiring a first nonpulsating pressure signal P c representative of tip clearance, sensing a second pressure P B substantially unaffected by tip clearance, forming an actual ratio of the acquired pressure and the sensed pressure, determining an error E having an actual component and a desired component, the actual component being a function of the actual ratio; and commanding a clearance control system to reduce the error.

    Abstract translation: 本发明是一种用于控制具有延伸穿过其中的流路的涡轮发动机中的叶片顶端间隙的方法，以及用于执行该方法的系统。 该方法包括获取表示顶端间隙的第一非脉动压力信号P SUB，感测基本上不受尖端间隙影响的第二压力P B B，形成获得的压力的实际比率 和感测到的压力，确定具有实际分量和期望分量的误差E，实际分量是实际比率的函数; 并指挥清关控制系统减少误差。

    CONFIGURATION OF THE BENT PARTS OF SERPENTINE COOLING CHANNELS FOR TURBINE SHROUDS
    3.
    发明申请
    CONFIGURATION OF THE BENT PARTS OF SERPENTINE COOLING CHANNELS FOR TURBINE SHROUDS 审中-公开
    用于涡轮风机的SERPENTINE冷却通道的弯管部件的配置

    公开(公告)号：WO1996023960A1

    公开(公告)日：1996-08-08

    申请号：PCT/US1996000426

    申请日：1996-01-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  THOMPSON, Ralph, J. ,  KANE, Daniel, E. ,  SUNSHINE, Robert, W.

    IPC: F01D25/12

    CPC classification number: F01D11/08 ,  F01D25/12

    Abstract: A turbine shroud segment for use in a gas turbine engine includes a serpentine channel along at least one axial edge of the segment. Various construction details are developed that disclose a channel for efficiently flowing cooling fluid through an axial edge of a shroud segment. In a particular embodiment, a turbine shroud segment includes a leading edge serpentine channel having a bend passage which includes a purge hole to avoid separating flow in the bend passage.

    Abstract translation: 用于燃气涡轮发动机的涡轮机护罩段包括沿着该段的至少一个轴向边缘的蛇形通道。 开发了各种结构细节，其公开了用于使冷却流体有效地流过护罩段的轴向边缘的通道。 在特定实施例中，涡轮机护罩段包括具有弯曲通道的前缘蛇形通道，该弯曲通道包括净化孔，以避免在弯曲通道中分离流动。

    MOUNTING AND SEALING ARRANGEMENT FOR A TURBINE SHROUD SEGMENT
    4.
    发明申请
    MOUNTING AND SEALING ARRANGEMENT FOR A TURBINE SHROUD SEGMENT 审中-公开
    涡轮分配器的安装和密封安装

    公开(公告)号：WO1995012056A1

    公开(公告)日：1995-05-04

    申请号：PCT/US1994009027

    申请日：1994-08-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  STAHL, Matthew ,  KANE, Daniel, E. ,  MURDOCK, James, R. ,  HADDAD, Donald, E.

    IPC: F01D11/08

    CPC classification number: F01D25/246 ,  F01D11/005 ,  F01D11/08

    Abstract: A shroud segment (42) for a gas turbine engine (12) includes a rail (54) engaged with adjacent support structure (52) to retain the segment (42) and to provide sealing between the segment (42) and the adjacent structure (52). The segment (42) is pressed against its support structure (52) by a resilient element (68) to provide effective sealing and retaining permitting differing thermal growth between the segment (42) and the support structure (52). In a particular embodiment, a shroud segment (42) includes a rail (54) along a forward edge. The rail (54) is engaged with a recess in the support structure (52) to retain the segment (42) and with a band (68) which positions the segment (42) and seals the forward edge.

    Abstract translation: 用于燃气涡轮发动机（12）的护罩段（42）包括与相邻的支撑结构（52）接合以保持段（42）并且在段（42）和相邻结构（42）之间提供密封的轨道（54） 52）。 通过弹性元件（68）将节段（42）压靠其支撑结构（52），以提供有效的密封和保持，从而允许段（42）和支撑结构（52）之间的不同热增长。 在特定实施例中，护罩区段（42）包括沿着前边缘的轨道（54）。 轨道（54）与支撑结构（52）中的凹部接合，以保持段（42）和定位段（42）并密封前缘的带（68）。

    COOLABLE OUTER AIR SEAL ASSEMBLY FOR A GAS TURBINE ENGINE
    5.
    发明申请
    COOLABLE OUTER AIR SEAL ASSEMBLY FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的可冷却外部空气密封组件

    公开(公告)号：WO1994018436A1

    公开(公告)日：1994-08-18

    申请号：PCT/US1994001286

    申请日：1994-02-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  KANE, Daniel, E. ,  HADDAD, Donald, E.

    IPC: F01D11/08

    CPC classification number: F01D11/08 ,  F01D11/005

    Abstract: A coolable outer air seal assembly (38) for a gas turbine engine (12) is disclosed. Various construction details are developed which provide an outer air seal assembly (38) comprised of a plurality of seal segments (46) including bumpers (62) adapted to maintain adequate cooling fluid flow through the clearance gap between adjacent seal segments (46). In one particular embodiment, each seal segment (46) includes a mating surface (64) having a plurality of bumpers (62) disposed adjacent to cooling fluid channel (58) outlets (72) and an axially extending ridge (88) disposed along the radially outer edge of the mating surface (64). The bumpers (62) extend circumferentially a distance Hb to maintain a minimum opening Gmin between adjacent seal segments (46) and extend a radial distance Wb to restrict fluid from flowing axially through the clearance gap. The ridge (88) extends radially outward to define in part a seal edge for engaging a feather seal (98).

    Abstract translation: 公开了一种用于燃气涡轮发动机（12）的可冷却外部空气密封组件（38）。 开发了各种构造细节，其提供由多个密封段（46）组成的外部空气密封组件（38），所述多个密封段（46）包括缓冲器（62），适于保持足够的冷却流体流过相邻密封段（46）之间的间隙。 在一个特定实施例中，每个密封段（46）包括配合表面（64），其具有邻近冷却流体通道（58）出口（72）设置的多个缓冲器（62）和沿着 配合表面（64）的径向外边缘。 保险杠（62）周向延伸一段距离Hb，以保持相邻的密封段（46）之间的最小开口Gmin，并且延伸径向距离Wb以限制流体轴向流过间隙。 脊（88）径向向外延伸，以部分地限定用于接合羽毛密封件（98）的密封边缘。

    TURBINE SHROUD SEGMENT WITH SERPENTINE COOLING CHANNELS
    6.
    发明申请
    TURBINE SHROUD SEGMENT WITH SERPENTINE COOLING CHANNELS 审中-公开
    涡轮风冷部分与SERPENTINE冷却通道

    公开(公告)号：WO1995027126A1

    公开(公告)日：1995-10-12

    申请号：PCT/US1995003567

    申请日：1995-03-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  THOMPSON, Ralph, J. ,  KANE, Daniel, E.

    IPC: F01D11/08

    CPC classification number: F01D11/08 ,  F01D25/12 ,  Y02T50/675

    Abstract: A turbine shroud segment (64) fixed by hooks (72) in the stator of a gas turbine engine includes a serpentine cooling channel (78, 82) along at least one axial edge of the segment. In a particular embodiment, a turbine shroud segment (64) includes a leading edge serpentine cooling channel (78) and a trailing edge serpentine cooling channel (82). Both serpentine channels (78, 82) include ducts (86, 92) that extend to the serpentine channels (78, 82) from a point inward of adjacent retaining hooks (72). Cooling fluid flowing onto the outward surface of the segments flows through the ducts (86, 92) and along the serpentine channels (78, 82) to cool the leading and trailing edges of the segments.

    Abstract translation: 通过钩（72）固定在燃气涡轮发动机的定子中的涡轮机护罩段（64）包括沿着该段的至少一个轴向边缘的蛇形冷却通道（78,82）。 在特定实施例中，涡轮机护罩段（64）包括前缘蛇形冷却通道（78）和后缘蛇形冷却通道（82）。 两个蛇形通道（78,82）包括从邻近的保持钩（72）内部的点延伸到蛇形通道（78,82）的管道（86,92）。 流过分段的外表面的冷却流体流过管道（86,92）并且沿着蛇形通道（78,82）流动以冷却段的前缘和后缘。

    COOLABLE OUTER AIR SEAL ASSEMBLY FOR A TURBINE
    7.
    发明申请
    COOLABLE OUTER AIR SEAL ASSEMBLY FOR A TURBINE 审中-公开
    用于涡轮机的可冷却外部空气密封组件

    公开(公告)号：WO1994012775A1

    公开(公告)日：1994-06-09

    申请号：PCT/US1993011350

    申请日：1993-11-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  STAHL, Matthew ,  HASTINGS, William, J. ,  KANE, Daniel, E. ,  MURDOCK, James, R. ,  DIERBERGER, James, A.

    IPC: F01D11/08

    CPC classification number: F01D11/122 ,  F05D2260/201 ,  F05D2260/202

    Abstract: An outer air seal assembly (44) cooled by a combination of impingement cooling and film cooling is disclosed. Various construction details are developed which provide impingement of cooling fluid on a radially outer side of an outer air seal assembly (44) and ejection of a film of cooling fluid over a radially inner surface (52) of the outer air seal assembly (44). In a particular embodiment, an outer air seal assembly (44) includes a substrate (54), an apertured cover (56) disposed outward of the substrate (54), and a layer of abradable material (58) extending radially inward of the substrate (54) and defining a flow surface (52). Cooling fluid is directed through the apertures (72), into a cavity (66), and impinges upon the outer surface of the substrate (54). A plurality of film cooling holes (76) extend through the substrate (54) and abradable layer (58) and provide fluid communication between the cavity (66) and flowpath (14). The cooling holes (76) are oriented to eject cooling in a film over the flow surface (52). In another embodiment, the cavity (66) includes a longitudinally extending chamber (112) disposed in an enlarged portion (108) of the air seal (46) to enhance cooling thereof and reduce stresses therewithin.

    Abstract translation: 公开了通过冲击冷却和薄膜冷却的组合冷却的外部空气密封组件（44）。 开发了各种结构细节，其提供了在外部空气密封组件（44）的径向外侧上的冷却流体的冲击和在外部空气密封组件（44）的径向内表面（52）上的冷却流体膜的喷射， 。 在特定实施例中，外部空气密封组件（44）包括衬底（54），设置在衬底（54）外侧的有孔盖（56）和沿着衬底的径向向内延伸的可磨损材料层 （54）并限定流动表面（52）。 冷却流体被引导通过孔（72）进入空腔（66），并且撞击在基底（54）的外表面上。 多个膜冷却孔（76）延伸穿过基底（54）和可磨损层（58），并提供空腔（66）和流路（14）之间的流体连通。 冷却孔（76）被定向成喷射在流动表面（52）上的膜中的冷却。 在另一个实施例中，空腔（66）包括设置在空气密封件（46）的扩大部分（108）中的纵向延伸腔室（112），以增强其冷却并降低其中的应力。

    MOUNTING AND SEALING ARRANGEMENT FOR A TURBINE SHROUD SEGMENT
    10.
    发明公开
    MOUNTING AND SEALING ARRANGEMENT FOR A TURBINE SHROUD SEGMENT 失效
    组件和密封系统用于涡轮环涂段

    公开(公告)号：EP0725888A1

    公开(公告)日：1996-08-14

    申请号：EP94926491.0

    申请日：1994-08-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： STAHL, Matthew ,  KANE, Daniel, E. ,  MURDOCK, James, R. ,  HADDAD, Donald, E.

    IPC: F01D5 ,  F01D11 ,  F01D25 ,  F02C7

    CPC classification number: F01D25/246 ,  F01D11/005 ,  F01D11/08

    Abstract: A shroud segment (42) for a gas turbine engine (12) includes a rail (54) engaged with adjacent support structure (52) to retain the segment (42) and to provide sealing between the segment (42) and the adjacent structure (52). The segment (42) is pressed against its support structure (52) by a resilient element (68) to provide effective sealing and retaining permitting differing thermal growth between the segment (42) and the support structure (52). In a particular embodiment, a shroud segment (42) includes a rail (54) along a forward edge. The rail (54) is engaged with a recess in the support structure (52) to retain the segment (42) and with a band (68) which positions the segment (42) and seals the forward edge.

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