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公开(公告)号：US5431532A
公开(公告)日：1995-07-11
申请号：US247741
申请日：1994-05-20
CPC分类号： F01D21/045 , F05D2220/327 , Y02T50/672
摘要： A blade containment system is disclosed which includes an annular casing positioned radially outward of the blades and in surrounding relationship therewith, the annular casing including a plurality of composite tapes bonded to the outer or inner radial surfaces thereof, wherein the composite tapes limit the propagation of cracks and holes formed in the annular casing.
摘要翻译： 公开了一种叶片容纳系统，其包括位于叶片的径向外侧的环形壳体并且与其周围的关系，环形壳体包括结合到其外径向表面或内径向表面的多个复合带，其中复合带限制了 裂缝和孔形成在环形壳体中。
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公开(公告)号：US5486086A
公开(公告)日：1996-01-23
申请号：US177297
申请日：1994-01-04
CPC分类号： F01D21/045 , F01D25/24 , F05D2220/327 , Y02T50/672
摘要： A blade containment system is disclosed which includes an annular casing positioned radially outward of the blades and in surrounding relationship therewith, the annular casing including a plurality of ribs on the outer radial surface thereof, wherein the ribs limit the propagation of cracks and holes formed in the annular casing.
摘要翻译： 公开了一种叶片容纳系统，其包括位于叶片的径向外侧的环形壳体并且与其周围的关系，所述环形壳体在其外径向表面上包括多个肋，其中所述肋限制了在 环形套管。
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公开(公告)号：US5333993A
公开(公告)日：1994-08-02
申请号：US024581
申请日：1993-03-01
申请人： Henry B. Stueber , Eric E. Baehre , Richard W. Albrecht , Christopher C. Glynn , Robert J. Hemmelgarn
发明人： Henry B. Stueber , Eric E. Baehre , Richard W. Albrecht , Christopher C. Glynn , Robert J. Hemmelgarn
CPC分类号： F01D11/025 , F01D11/001 , F01D11/04
摘要： A stator seal assembly for a gas turbine engine of a type having a high pressure compressor section and a high pressure turbine section, the stator seal having a seal segment extending between a stator vane support structure and disk seal teeth, the stator seal segment having an arm for forming a cavity, a retaining segment attached to the seal segment and the arm for sealing the cavity to form a dead air space, a control ring located in the cavity having a coefficient of thermal expansion lower than a coefficient of thermal expansion for the seal segment, and a honeycomb pad located between the arm and the seal teeth, whereby thermal expansion clearance between the stator vane and the rotor disk is minimized.
摘要翻译： 一种用于具有高压压缩机部分和高压涡轮部分类型的燃气涡轮发动机的定子密封组件，所述定子密封件具有在定子叶片支撑结构和盘密封齿之间延伸的密封段，所述定子密封段具有 用于形成空腔的臂，附接到密封段的保持段和用于密封空腔以形成死空间的臂，位于空腔中的控制环，其热膨胀系数低于热膨胀系数 密封段和位于臂和密封齿之间的蜂窝垫，由此定子叶片和转子盘之间的热膨胀间隙最小化。
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公开(公告)号：US5292227A
公开(公告)日：1994-03-08
申请号：US988637
申请日：1992-12-10
CPC分类号： F01D9/065 , F01D25/162
摘要： A turbine frame includes first and second coaxially disposed rings having a plurality of circumferentially spaced apart struts extending therebetween. A plurality of clevises join respective first ends of the struts to the first ring for removably joining the struts thereto. Each of the clevises includes a base removably fixedly joined to the first ring, and a pair of legs extending away from the base and spaced apart to define a U-shaped clevis slot receiving the strut first end. The first strut end is removably fixedly joined to the clevis legs by a pair of expansion bolts. The clevis base includes a central aperture aligned with a first port in the first ring for providing access therethrough. And, the strut first end abuts the first ring for carrying compressive loads therebetween and providing a seal therewith.
摘要翻译： 涡轮机框架包括第一和第二同轴设置的环，其具有在其间延伸的多个周向间隔开的支柱。 多个U形夹将支柱的相应的第一端连接到第一环，用于将支柱可拆卸地连接到其上。 每个夹头包括可移除地固定地连接到第一环的基座和一对从基部延伸并间隔开的一对腿，以限定接纳支柱第一端的U形U形夹。 第一支柱端通过一对膨胀螺栓可拆卸地固定在U形夹腿上。 U形夹底座包括与第一环中的第一端口对准的中心孔，用于提供通过其中的通路。 并且，支柱第一端邻接第一环以在其间承载压缩载荷并且提供与其的密封。
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公开(公告)号：US5357744A
公开(公告)日：1994-10-25
申请号：US86406
申请日：1993-07-01
IPC分类号： F01D9/04 , F01D9/06 , F01D11/00 , F01D25/16 , F01D25/24 , F02C7/00 , F02C7/20 , F02C7/28 , F16B1/00 , F16B2/06 , F16B43/02
CPC分类号： F01D25/243 , F01D25/162 , F01D25/246 , F01D9/065 , F02C7/20 , F16B43/02 , F16B43/025 , F16B2/065 , F16B2001/0078
摘要： A turbine flowpath assembly includes a plurality of circumferentially spaced apart airfoils disposed within an annular outer casing. Each of the airfoils includes outer and inner integral bands. A plurality of flowpath outer and inner panels are disposed between adjacent ones of the bands and circumferentially overlap the bands. The panels and bands are joined together at the respective overlaps for allowing circumferential movement therebetween while providing sealing.
摘要翻译： 涡轮流路组件包括设置在环形外壳内的多个周向间隔开的翼片。 每个翼型件包括外部和内部整体带。 多个流路外部和内部面板设置在相邻的带之间并且周向地与带重叠。 面板和带在相应的重叠处连接在一起，以允许其间的周向移动，同时提供密封。
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公开(公告)号：US06357237B1
公开(公告)日：2002-03-19
申请号：US09398558
申请日：1999-09-17
IPC分类号： F02C100
CPC分类号： F23R3/28 , F23D11/36 , F23D11/402 , F23D2206/10 , F23D2209/30
摘要： A fuel injection assembly for a gas turbine engine combustor, including at least one fuel stem, a plurality of concentrically disposed tubes positioned within each fuel stem, wherein a cooling supply flow passage, a cooling return flow passage, and a tip fuel flow passage are defined thereby, and at least one fuel tip assembly connected to each fuel stem so as to be in flow communication with the flow passages, wherein an active cooling circuit for each fuel stem and fuel tip assembly is maintained by providing all active fuel through the cooling supply flow passage and the cooling return flow passage during each stage of combustor operation. The fuel flowing through the active cooling circuit is then collected so that a predetermined portion thereof is provided to the tip fuel flow passage for injection by the fuel tip assembly.
摘要翻译： 一种用于燃气涡轮发动机燃烧器的燃料喷射组件，其包括至少一个燃料杆，位于每个燃料杆内的多个同心设置的管，其中，冷却供给流路，冷却回流通道和末端燃料流动通道 以及与每个燃料杆连接以便与流动通道流动连通的至少一个燃料末端组件，其中通过提供所有活性燃料通过冷却来维持每个燃料杆和燃料末端组件的主动冷却回路 在燃烧器运行的每个阶段，供应流通道和冷却回流通道。 然后，流过主动冷却回路的燃料被收集，使得其预定部分被提供给燃料末端组件用于喷射的末端燃料流动通道。
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公开(公告)号：US5713721A
公开(公告)日：1998-02-03
申请号：US644019
申请日：1996-05-09
申请人： Christopher C. Glynn , Poul D. Pedersen , Frederick M. Miller , Roger C. Walker , Sang Yeng Park , Clifford C. May
发明人： Christopher C. Glynn , Poul D. Pedersen , Frederick M. Miller , Roger C. Walker , Sang Yeng Park , Clifford C. May
CPC分类号： F01D5/323 , F01D5/326 , F04D29/322
摘要： One form of a retention system includes a pair of aft segments of 180.degree. in length disposed in annular grooves about a compressor spool, the segments having radial projections against which the aft end faces of the base portions of rotor blades abut. The blade base portions are shaped and are received in complementary-shaped slots of the spool. The forward retention system includes a plurality of arcuate segments approximately 30.degree. in length disposed in grooves adjacent the forward end faces of the blades. With the exception of the final pair of blades, the blade base portions thereof are located in the axial complementary slots in pairs, with each forward arcuate segment, except the final segment, being disposed in the groove at a circumferentially spaced location and displaced circumferentially to abut the forward end faces. The final arcuate segment is radially reduced and disposed in the remaining portion of the groove to lie flush with the spool. The base portions of the final blades are axially inserted over the final segments and the latter is displaced radially outwardly and pinned to abut the forward end faces of the final blade base portions. In another form, tabs project forwardly or rearwardly from the base portions of the blades. The tabs have holes in registry with corresponding holes in the blade slot for receiving pins thereby preventing axial movement of the blades relative to the spool.
摘要翻译： 保持系统的一种形式包括长度为180度的一对后部，其围绕压缩机线轴设置在环形槽中，所述段具有径向突出部，转子叶片的基部的后端面邻接。 叶片基部成形并被容纳在卷轴的互补形状的槽中。 前保持系统包括多个大约30度的弧形段，其设置在与刀片的前端面相邻的凹槽中。 除了最后一对叶片之外，其叶片基座部分成对地位于轴向互补的槽中，除了最后的部分之外，每个前部的弧形段在周向间隔开的位置设置在槽中， 靠近前端面。 最终弧形段径向减小并设置在凹槽的剩余部分中以与卷轴齐平。 最终叶片的基部轴向插入到最终的段上，并且后端径向向外移动并固定以邻接最终叶片基部的前端面。 在另一种形式中，翼片从叶片的基部向前或向后突出。 突片具有与刀片槽中的相应孔对准的孔，用于接收销，从而防止刀片相对于线轴的轴向移动。
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公开(公告)号：US5211407A
公开(公告)日：1993-05-18
申请号：US876602
申请日：1992-04-30
IPC分类号： F01D11/00
CPC分类号： F01D11/006
摘要： A seal assembly for use in a compressor stage of a turbine engine having a rotor disk which is attached to a plurality of rotor blades. Each rotor blade has an axially oriented dovetail attachment which connects to the rotor disk. Each rotor blade has an aftward side which is in contact with a high pressure region and a forward side which is in contact with a low pressure region. A plurality of seal segments form an annular ring located radially inward from the plurality of rotor blades. Each seal segment has an offset center of gravity which causes each seal segment to be securely attached to the rotor disk as centrifugal forces act upon each seal segment during rotation.
摘要翻译： 一种用于涡轮发动机的压缩机级的密封组件，其具有附接到多个转子叶片的转子盘。 每个转子叶片具有连接到转子盘的轴向定向的燕尾座附件。 每个转子叶片具有与高压区域接触的向前侧和与低压区域接触的前侧。 多个密封段形成从多个转子叶片径向向内定位的环形圈。 每个密封段具有偏移重心，这使得每个密封段在转动过程中随着离心力作用在每个密封段上而牢固地附接到转子盘上。
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公开(公告)号：US06676369B2
公开(公告)日：2004-01-13
申请号：US10106401
申请日：2002-03-26
IPC分类号： F01D1102
CPC分类号： F16J15/442 , F01D11/025
摘要： A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.
摘要翻译： 燃气涡轮发动机抽吸面密封件包括可旋转的发动机构件和不可旋转的发动机构件以及它们之间的泄漏路径。 围绕中心线环绕的环形大致平面的可旋转和不可旋转的气体支承面表面分别可操作地与可旋转和不可旋转的发动机构件相关联。 径向内齿和外齿环沿穿过泄漏路径并朝着气体支承面表面中的第二个轴向延伸远离可旋转和不可旋转的气体支承面表面中的第一个。 使用拉脱偏压装置来推动内齿轮和外齿环轴向远离第二气体支承面表面。 可旋转的发动机构件可以是安装在转子盘上的侧板，并且不可旋转的发动机构件安装在可移动地支撑在固定面密封支撑结构上的可平移活塞上。
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公开(公告)号：US06240719B1
公开(公告)日：2001-06-05
申请号：US09207818
申请日：1998-12-09
IPC分类号： F02K304
CPC分类号： F01D21/045 , F01D21/04 , F01D25/16 , F01D25/162 , F05B2260/3011
摘要： A support structure for a gas turbine engine includes a support arm (214, 216) extending between a low pressure shaft (202) and a rotor. The support arm includes a fuse (220) having a low failure point. A high pressure stub shaft (270) axially and radially supports the low pressure shaft (202) after fuse failure. An axial gap (A) between a portion of the low pressure shaft and the stub shaft permits movement of the low pressure shaft after fuse failure. A radial gap (B) between the stub shaft (270) and the low pressure shaft (202) allows radial deflection of the low pressure rotor system after fuse failure.
摘要翻译： 用于燃气涡轮发动机的支撑结构包括在低压轴（202）和转子之间延伸的支撑臂（214,216）。 支撑臂包括具有低故障点的保险丝（220）。 保险丝故障后，高压短轴（270）轴向和径向地支撑低压轴（202）。 在低压轴的一部分和短轴之间的轴向间隙（A）允许熔丝故障后低压轴的移动。 短轴（270）和低压轴（202）之间的径向间隙（B）允许在保险丝故障之后低压转子系统的径向偏转。
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