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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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42.发明授权Mid-section of a can-annular gas turbine engine with a cooling system for the transition 有权具有用于过渡的冷却系统的罐环式燃气涡轮发动机的中段公开(公告)号：US09206699B2
公开(公告)日：2015-12-08
申请号：US13408061
申请日：2012-02-29
申请人： David J. Wiebe , Jose L. Rodriguez
发明人： David J. Wiebe , Jose L. Rodriguez
摘要： A cooling system is provided for a transition (420) of a gas turbine engine (410). The cooling system includes a cowling (460) configured to receive an air flow (111) from an outlet of a compressor section of the gas turbine engine (410). The cowling (460) is positioned adjacent to a region of the transition (420) to cool the transition region upon circulation of the air flow within the cowling (460). The cooling system further includes a manifold (121) to directly couple the air flow (111) from the compressor section outlet to an inlet (462) of the cowling (460). The cowling (460) is configured to circulate the air flow (111) within an interior space (426) of the cowling (460) that extends radially outward from an inner diameter (423) of the cowling to an outer diameter (424) of the cowling at an outer surface.
摘要翻译： 为燃气涡轮发动机（410）的过渡（420）提供冷却系统。 冷却系统包括构造成从燃气涡轮发动机（410）的压缩机部分的出口接收空气流（111）的整流罩（460）。 整流罩（460）定位成邻近过渡区域（420），以在气流（460）内的空气流循环时冷却过渡区域。 冷却系统还包括将空气流（111）从压缩机部分出口直接联接到整流罩（460）的入口（462）的歧管（121）。 整流罩（460）构造成使得空气流（111）在整流罩（460）的内部空间（426）内循环，该整流罩（460）从整流罩的内径（423）径向向外延伸到外壳 在外表面的整流罩。
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43.发明授权Fuel nozzle assembly for use as structural support for a duct structure in a combustor of a gas turbine engine 有权燃料喷嘴组件，其用作燃气涡轮发动机的燃烧器中的管道结构的结构支撑公开(公告)号：US08991192B2
公开(公告)日：2015-03-31
申请号：US12566222
申请日：2009-09-24
申请人： David J. Wiebe , Timothy A. Fox
发明人： David J. Wiebe , Timothy A. Fox
摘要： A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion gases flowing within the combustor apparatus. The fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel. A fuel injector of the fuel nozzle assembly is provided in the inner volume of the outer housing and defines a fuel passage therein. The fuel passage is in fluid communication with the fuel supply channel of the fuel manifold for distributing the fuel from the fuel supply channel into the flow passage of the duct structure.
摘要翻译： 一种用于燃气涡轮发动机的燃烧器装置的燃料喷嘴组件。 燃料喷嘴组件的外壳包括内部容积并且在管道结构和燃料歧管之间提供直接的结构连接。 管道结构限定了在燃烧器装置内流动的燃烧气体的流动通道。 燃料歧管在其中限定了与燃料源流体连通的燃料供应通道。 燃料喷嘴组件的燃料喷射器设置在外部壳体的内部容积中并且在其中限定燃料通道。 燃料通道与燃料歧管的燃料供应通道流体连通，用于将燃料从燃料供应通道分配到管道结构的流动通道中。
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公开(公告)号：US20150056068A1
公开(公告)日：2015-02-26
申请号：US13974147
申请日：2013-08-23
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D5/06 , F01D5/066 , F01D11/003 , F01D11/005 , F01D11/008 , F02C7/28
摘要： A circumferentially extending sealing band is located within sealing band receiving slots formed in adjacent turbine engine disks. The sealing band includes a plurality of seal strips forming overlap joints defined by overlapping end portions, each formed by a tongue portion extending from a seal face of one seal strip past a seal face of the adjacent seal strip, along a radially inward facing side of the adjacent seal strip. A joint gap is defined within at least one overlap joint between the seal face of the one seal strip and the seal face of the adjacent strip, and a spacer is affixed to the one seal strip and is located at a position within the joint gap between the seal faces to limit circumferential movement of the seal faces toward each other.
摘要翻译： 周向延伸的密封带位于形成在相邻的涡轮引擎盘中的密封带接收槽内。 密封带包括形成由重叠端部限定的重叠接头的多个密封条，每个密封条由从一个密封条的密封面延伸穿过相邻密封条的密封面的舌部形成，该舌部沿着径向向内的侧面 相邻密封条。 在一个密封条的密封面和相邻条的密封面之间的至少一个重叠接合部内限定了接合间隙，并且间隔件固定到一个密封条上，并且位于第一密封条之间的接合间隙内的位置 密封面面对以限制密封面朝向彼此的周向移动。
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公开(公告)号：US08959888B2
公开(公告)日：2015-02-24
申请号：US13305120
申请日：2011-11-28
摘要： An emissions control system for a gas turbine engine including a flow-directing structure (24) that delivers combustion gases (22) from a burner (32) to a turbine. The emissions control system includes: a conduit (48) configured to establish fluid communication between compressed air (22) and the combustion gases within the flow-directing structure (24). The compressed air (22) is disposed at a location upstream of a combustor head-end and exhibits an intermediate static pressure less than a static pressure of the combustion gases within the combustor (14). During operation of the gas turbine engine a pressure difference between the intermediate static pressure and a static pressure of the combustion gases within the flow-directing structure (24) is effective to generate a fluid flow through the conduit (48).
摘要翻译： 一种用于燃气涡轮发动机的排放控制系统，其包括将燃烧气体（22）从燃烧器（32）输送到涡轮机的流动引导结构（24）。 排放物控制系统包括：导管（48），其配置成建立压缩空气（22）与导流结构（24）内的燃烧气体之间的流体连通。 压缩空气（22）设置在燃烧器头端的上游位置处，并且具有小于燃烧器（14）内的燃烧气体的静压力的中间静压力。 在燃气涡轮发动机的操作期间，导流结构（24）内的中间静压与燃烧气体的静压之间的压力差有效地产生通过导管（48）的流体流。
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公开(公告)号：US08549859B2
公开(公告)日：2013-10-08
申请号：US12233903
申请日：2008-09-19
IPC分类号： F02C7/22
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.
摘要翻译： 燃气涡轮发动机中的燃烧装置包括用于接收空气的燃烧器壳体，与燃烧器壳体相关联的燃料喷射系统，第一燃料供应结构和屏蔽结构。 燃料供应结构与燃料源流体连通，用于将燃料从燃料源输送到燃料喷射系统，并且包括第一燃料供应元件，其包括沿着沿轴向方向具有部件的第一路径延伸的第一部分，以及 第二部分沿着沿圆周方向具有部件的第二路径从第一部分延伸。 屏蔽结构与第一燃料供应元件的第二部分的至少一部分相关联。
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公开(公告)号：US20130152543A1
公开(公告)日：2013-06-20
申请号：US13326392
申请日：2011-12-15
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F02C3/14
CPC分类号： F02C3/14 , F01D1/08 , F01D9/023 , F05D2250/313
摘要： A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner surfaces (34) that are adjacent to combustion gases (40). The inner surfaces (34) of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades (38), a plurality of discrete flows of the combustion gases (40). The array inner surfaces (34) define respective combustion gas flow axes (20). Each combustion gas flow axis (20) is straight from a point of ignition until no longer bound by the array inner surfaces (34), and each combustion gas flow axis (20) intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades (38).
摘要翻译： 一种燃气涡轮发动机（10），包括：具有径向流入叶轮叶片（38）的涡轮机; 以及一组先进的过渡燃烧器组件，其围绕径向流入叶轮（38）周向布置并具有与燃烧气体（40）相邻的内表面（34）。 阵列的内表面（34）构造成加速和定向，以直接输送到径向流入叶轮（38）上，燃烧气体（40）的多个离散流。 阵列内表面（34）限定相应的燃烧气体流动轴线（20）。 每个燃烧气体流动轴线（20）从点火直线直到不再受阵列内表面（34）的约束，并且每个燃烧气体流动轴线（20）与由扫描线 径向流入叶轮叶片（38）。
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公开(公告)号：US20130133330A1
公开(公告)日：2013-05-30
申请号：US13305120
申请日：2011-11-28
IPC分类号： F23R3/42
摘要： An emissions control system for a gas turbine engine including a flow-directing structure (24) that delivers combustion gases (22) from a burner (32) to a turbine. The emissions control system includes: a conduit (48) configured to establish fluid communication between compressed air (22) and the combustion gases within the flow-directing structure (24). The compressed air (22) is disposed at a location upstream of a combustor head-end and exhibits an intermediate static pressure less than a static pressure of the combustion gases within the combustor (14). During operation of the gas turbine engine a pressure difference between the intermediate static pressure and a static pressure of the combustion gases within the flow-directing structure (24) is effective to generate a fluid flow through the conduit (48).
摘要翻译： 一种用于燃气涡轮发动机的排放控制系统，其包括将燃烧气体（22）从燃烧器（32）输送到涡轮机的流动引导结构（24）。 排放物控制系统包括：导管（48），其配置成建立压缩空气（22）与导流结构（24）内的燃烧气体之间的流体连通。 压缩空气（22）设置在燃烧器头端的上游位置处，并且具有小于燃烧器（14）内的燃烧气体的静压力的中间静压力。 在燃气涡轮发动机的操作期间，导流结构（24）内的中间静压与燃烧气体的静压之间的压力差有效地产生通过导管（48）的流体流。
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公开(公告)号：US20130011242A1
公开(公告)日：2013-01-10
申请号：US13177701
申请日：2011-07-07
IPC分类号： F01D25/16
CPC分类号： F01D25/28 , F01D25/30 , F05D2250/314
摘要： A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.
摘要翻译： 一种燃气涡轮发动机中的支撑结构，包括内环形壁和限定环形流路的外环形壁，容纳限定流路的结构的壳体和容纳从内环径向向内定位的转子轴轴承的轴承室 壁。 支撑结构包括多个周向间隔开的径向支撑构件，其从壳体处的外部安装连接件径向向内延伸到轴承隔室壳体处的内部安装连接。 径向支撑构件为转子轴承上的径向轴承负载提供结构支撑。 多个周向间隔开的轴向支撑构件从壳体处的外部安装连接件径向和轴向向内延伸到位于在轴承隔室壳体和内部环形壁处的连接位置之间径向延伸的环形结构上的内部安装连接件。
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公开(公告)号：US20110056206A1
公开(公告)日：2011-03-10
申请号：US12555134
申请日：2009-09-08
申请人： David J. Wiebe
发明人： David J. Wiebe
摘要： A fuel injector in a combustor apparatus of a gas turbine engine. An outer wall of the injector defines an interior volume in which an intermediate wall is disposed. A first gap is formed between the outer wall and the intermediate wall. The intermediate wall defines an internal volume in which an inner wall is disposed. A second gap is formed between the intermediate wall and the inner wall. The second gap receives cooling fluid that cools the injector. The cooling fluid provides convective cooling to the intermediate wall as it flows within the second gap. The cooling fluid also flows through apertures in the intermediate wall into the first gap where it provides impingement cooling to the outer wall and provides convective cooling to the outer wall. The inner wall defines a passageway that delivers fuel into a liner downstream from a main combustion zone.
摘要翻译： 燃气涡轮发动机的燃烧器装置中的燃料喷射器。 注射器的外壁限定内部容积，其中设置中间壁。 在外壁和中间壁之间形成第一间隙。 中间壁限定了内壁的内部容积。 在中间壁和内壁之间形成第二间隙。 第二间隙接收冷却喷射器的冷却流体。 冷却流体在第二间隙内流动时向中间壁提供对流冷却。 冷却流体还通过中间壁中的孔流入第一间隙，在第一间隙中，其向外壁提供冲击冷却并向外壁提供对流冷却。 内壁限定了将燃料输送到主燃烧区下游的衬套的通道。
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