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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）。
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Patent Agency Ranking
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
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。
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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.
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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公开(公告)号：EP0682741A1
公开(公告)日：1995-11-22
申请号：EP94908714.0
申请日：1994-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KANE, Daniel, E. , HADDAD, Donald, E.
IPC: F01D11
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).
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公开(公告)号：EP0682741B1
公开(公告)日：1996-09-11
申请号：EP94908714.2
申请日：1994-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KANE, Daniel, E. , HADDAD, Donald, E.
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).
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公开(公告)号：EP0725888B1
公开(公告)日：2000-04-19
申请号：EP94926491.5
申请日：1994-08-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： STAHL, Matthew , KANE, Daniel, E. , MURDOCK, James, R. , HADDAD, Donald, E.
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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