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公开(公告)号：US08230688B2
公开(公告)日：2012-07-31
申请号：US12420149
申请日：2009-04-08
IPC分类号： F02C3/00
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F05D2250/324 , F23R3/425 , F23R3/46
摘要： An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.
摘要翻译： 用于将罐体环形燃气轮机内燃机的燃烧器的气体输送到包括第一排涡轮叶片的涡轮机第一级部分的装置，该装置包括用于每个燃烧器的流动导向结构，其中每个流动导向结构包括 直线路径和环形室端部，其中环形室端部一起限定了用于将气流输送到涡轮机第一级段的环形室，其中气体通过相应的直线路径从相应的燃烧器流动，并且作为相应的直线 气体流动，并且其中所述环形室被构造成沿着相应的剪切平面联合相应的直的气体流以形成奇异的环形气流，并且其中所述环形室被构造成在所述单个环形气流 气流离开环形室到第一排叶片。
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公开(公告)号：US20100077719A1
公开(公告)日：2010-04-01
申请号：US12420149
申请日：2009-04-08
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F05D2250/324 , F23R3/425 , F23R3/46
摘要： An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.
摘要翻译： 用于将罐体环形燃气轮机内燃机的燃烧器的气体输送到包括第一排涡轮叶片的涡轮机第一级部分的装置，该装置包括用于每个燃烧器的流动导向结构，其中每个流动导向结构包括 直线路径和环形室端部，其中环形室端部一起限定了用于将气流输送到涡轮机第一级段的环形室，其中气体通过相应的直线路径从相应的燃烧器流动，并且作为相应的直线 气体流动，并且其中所述环形室被构造成沿着相应的剪切平面联合相应的直的气体流以形成奇异的环形气流，并且其中所述环形室被构造成在所述单个环形气流 气流离开环形室到第一排叶片。
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公开(公告)号：US08276389B2
公开(公告)日：2012-10-02
申请号：US13096041
申请日：2011-04-28
申请人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
发明人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
IPC分类号： F02C3/00
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F23R3/425 , F23R3/46 , F23R3/60
摘要： An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.
摘要翻译： 一种用于将燃烧气体从多个罐环形燃烧器输送到燃气涡轮发动机的涡轮机第一级叶片部分的装置（10），所述装置（10）包括多个互连的集成出口件（IEP）部分（16），其限定 与涡轮机第一级叶片部分上游的燃气涡轮发动机纵向轴线（20）同心取向的环形室（18）。 每个相应的IEP（16）包括第一流路部分（40），其沿着相应的公共轴线（22）接收并完全限定来自相应的罐环形燃烧器的第一流动，并且将部分有界的第一流体递送到下游相邻 IEP部分（42）。 每个相应的IEP还包括第二流路部分（112），其接收来自上游相邻的IEP（66）的部分界定的第二流，并将第二流的至少一部分输送到涡轮机第一级叶片部分。
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公开(公告)号：US20110203282A1
公开(公告)日：2011-08-25
申请号：US13096041
申请日：2011-04-28
申请人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
发明人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
IPC分类号： F02C3/14
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F23R3/425 , F23R3/46 , F23R3/60
摘要： An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.
摘要翻译： 一种用于将燃烧气体从多个罐环形燃烧器输送到燃气涡轮发动机的涡轮机第一级叶片部分的装置（10），所述装置（10）包括多个互连的集成出口件（IEP）部分（16），其限定 与涡轮机第一级叶片部分上游的燃气涡轮发动机纵向轴线（20）同心取向的环形室（18）。 每个相应的IEP（16）包括第一流路部分（40），其沿着相应的公共轴线（22）接收并完全限定来自相应的罐环形燃烧器的第一流动，并且将部分有界的第一流体递送到下游相邻 IEP部分（42）。 每个相应的IEP还包括第二流路部分（112），其接收来自上游相邻的IEP（66）的部分界定的第二流，并将第二流的至少一部分输送到涡轮机第一级叶片部分。
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公开(公告)号：US09322335B2
公开(公告)日：2016-04-26
申请号：US13834185
申请日：2013-03-15
CPC分类号： F02C7/20 , F01D9/023 , F05D2250/25 , F23R3/425
摘要： An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.
摘要翻译： 一种具有入口喉部（67）的出口件（66），其将来自燃烧器（63）的通道（82）中的燃烧气体流（36A）传导到馈送第一叶片部分（37）的环形室（68） 的燃气轮机（26）。 出口件还包括形成环形室的周向段的出口部分（69）。 出口部分通过铰链（78A，78B，80A，80B）与相邻的出口部分相互连接。 每个铰链可以具有平行于涡轮机的中心线（21）的铰链轴线（82A，82B）。 相应的气体流（36A）由出口件的组件（60）构成，以将进料腔（68）会聚成均匀的螺旋流，其以最小的周向变化力驱动第一叶片部分。
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6.发明授权公开(公告)号：US09528706B2
公开(公告)日：2016-12-27
申请号：US14105313
申请日：2013-12-13
申请人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
发明人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
CPC分类号： F23R3/46 , F04D29/542 , F04D29/545 , F04D29/547 , F23R3/02 , F23R3/04 , F23R3/425
摘要： A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
摘要翻译： 一种燃气涡轮发动机罐环式燃烧装置（10），包括：轴向压缩机（82），其可操作以沿旋转方向（60）旋转; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）; 配置成从扩散器接收压缩空气的增压室（22） 多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以被切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向偏移 方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对所述增压室中的压缩空气施加周向运动。
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公开(公告)号：US09388738B2
公开(公告)日：2016-07-12
申请号：US13252325
申请日：2011-10-04
摘要： A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).
摘要翻译： 一种用于罐式环形燃气涡轮发动机的壳体，包括：压缩空气部分（40），跨过最后一排压缩机叶片（26）和第一排涡轮叶片（28），压缩空气部分（40）具有 多个开口（50）穿过其中，其中单个燃烧器/先进管道组件（64）延伸穿过每个开口（50）; 以及与每个开口（50）相关联的一个顶帽（68），其构造成包围相关联的燃烧器/先进管道组件（64）并密封所述开口（50）。 由压缩空气部分（40）包围的体积不大于在上游端（56）处由最后一排压缩机叶片（26）处的壳体的内径限定的平截头体（54）的体积，并且在 在第一排涡轮叶片（28）处通过壳体的内径的下游端（60）。
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公开(公告)号：US09200565B2
公开(公告)日：2015-12-01
申请号：US13310855
申请日：2011-12-05
CPC分类号： F02C3/14 , F01D25/24 , F01D25/243 , F01D25/285 , F05D2230/70 , F05D2230/72 , F23R3/46
摘要： A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).
摘要翻译： 一种罐式环形工业燃气涡轮发动机，包括：跨过压缩机部分（82），燃烧部分（84），涡轮部分（86）的单件转子轴; 和具有构成为完全箍的部分（28）的燃烧部分壳体（10）。 当燃烧部分壳体与发动机分离并移动到维修位置以允许进入发动机内部时，定位夹具（98）用于支撑压缩机部分壳体（83）和涡轮部分壳体（87） 。
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公开(公告)号：US07862296B2
公开(公告)日：2011-01-04
申请号：US11844778
申请日：2007-08-24
IPC分类号： F03B3/14
CPC分类号： F01D9/042 , F05B2260/301 , F05D2230/644 , F05D2250/314 , F05D2260/96 , Y10S416/50
摘要： A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.
摘要翻译： 涡轮机叶片附接系统，被配置为消除涡轮叶片相对于涡轮叶片承载器的运动。 涡轮叶片附接系统可以包括附接到涡轮机翼型的基座。 基座可以被构造成沿着与翼型件的纵向轴线大致不平行和非正交的平面接触楔形支撑件。 螺栓可以将基座与楔形支撑件连接。 螺栓可以改变基座中的通道与外部支承表面之间的距离。 涡轮叶片可以定位在叶片载体中，使得从叶片载体延伸的舌片定位在通道中。 当螺栓前进时，楔形支撑件沿着基座的支撑表面横向移动，并且通道接合舌片，从而防止涡轮叶片的运动。
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10.发明授权Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier 有权燃气轮机环形腔和涡轮叶片架之间的燃气轮机结构安装公开(公告)号：US09470422B2
公开(公告)日：2016-10-18
申请号：US14059521
申请日：2013-10-22
CPC分类号： F23R3/60 , F01D9/023 , F05D2260/30 , F23R3/46
摘要： A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.
摘要翻译： 一种燃气涡轮发动机管道装置（10），包括：环形室（14），其构造成容纳源自相应罐燃烧器的多个不连续的燃烧气体流，并将离散流输送到涡轮入口环，其中环形室 包括内径（52）和外径（60）; 外径安装装置（34）被构造成允许相对径向移动并且防止外径与涡轮叶片载体（20）之间的相对轴向和周向移动; 以及内径安装装置（36），其包括固定到所述涡轮机叶片承载件的支架（64），其中所述支架构造成允许所述内径径向与所述外径径向移动，并且防止所述内径相对于 外径。
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