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公开(公告)号：US06702547B2
公开(公告)日：2004-03-09
申请号：US10120806
申请日：2002-04-11
申请人： Peter Tiemann
发明人： Peter Tiemann
IPC分类号： F01D906
CPC分类号： F01D5/187 , F01D5/085 , F01D25/12 , F02C7/18 , F05D2260/205 , F05D2260/232
摘要： In a gas turbine (1) having a number of rotor blades (12) in each case combined into rows of rotor blades and arranged on a turbine shaft (8), and having a number of stator blades (14) in each case combined into rows of stator blades and connected to a turbine casing, a particularly high efficiency is simply to be achieved with reliable cooling of the turbine blades (12), (14). For this purpose, at least some of the stator blades (14) have an inlet (48) for a cooling medium at their free end facing the turbine shaft (8).
摘要翻译： 在具有多个转子叶片（12）的燃气轮机（1）中，每个壳体组合成行的转子叶片并布置在涡轮机轴（8）上，并且每个壳体中的多个定子叶片（14）组合成 定子叶片的一排并连接到涡轮机壳体上，特别高的效率简单地通过涡轮叶片（12），（14）的可靠冷却来实现。 为此目的，至少一些定子叶片（14）在其面向涡轮轴（8）的自由端具有用于冷却介质的入口（48）。
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公开(公告)号：US06599092B1
公开(公告)日：2003-07-29
申请号：US10039719
申请日：2002-01-04
IPC分类号： F01D906
CPC分类号： F01D5/187 , F05D2240/10 , F05D2260/22141 , Y02T50/676
摘要： A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge, forming a plurality of slots in the pressure side of the airfoil extending towards the trailing edge, and extending a plurality of pins arranged in rows between the airfoil suction and pressure sides, such that at each of a first row of pins has a substantially elliptical cross-sectional area, wherein the first row of pins is between the remaining rows of pins and the airfoil pressure side slots.
摘要翻译： 一种用于制造用于燃气涡轮发动机的喷嘴的方法有助于延长喷嘴的使用寿命。 喷嘴包括翼型件。 所述方法包括形成所述翼型件以包括吸入侧和连接在前缘和后缘处的压力侧，在所述翼型件的压力侧中形成多个狭槽，所述多个狭槽朝向所述后缘延伸，并且延伸多个销布置 在翼型吸力和压力侧之间的行中，使得在第一排销的每一个具有基本上椭圆形的横截面积，其中第一排销在剩余的销排和翼型压力侧槽之间。
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公开(公告)号：US06572329B2
公开(公告)日：2003-06-03
申请号：US10004476
申请日：2001-11-16
申请人： Peter Tiemann
发明人： Peter Tiemann
IPC分类号： F01D906
CPC分类号： F01D5/188 , F05D2260/201 , F05D2260/205 , F05D2260/2322
摘要： A gas turbine blade is used for closed steam cooling. A partition, preferably designed as a metal sheet, divides a first part cavity in the axial direction. This is done in such a way that steam is capable of being guided out of the first subspace into an inlet edge cavity and from this into a second subspace with an impact-cooling effect, This has the advantage that closed steam cooling is designed to be particularly simple and cost-effective in manufacturing terms, while at the same time the inlet edge has an aerodynamically favorable shape.
摘要翻译： 燃气轮机叶片用于封闭蒸汽冷却。 优选地设计为金属片的分隔件在轴向方向上分割第一部分空腔。 这样做的方式是使得蒸汽能够被引导出第一子空间进入入口边缘空腔，并且由此形成具有冲击冷却效果的第二子空间。这具有将闭合蒸汽冷却设计成为 在制造方面特别简单和成本有效，同时入口边缘具有空气动力学良好的形状。
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公开(公告)号：US06554563B2
公开(公告)日：2003-04-29
申请号：US09928763
申请日：2001-08-13
IPC分类号： F01D906
CPC分类号： F01D5/189 , F05D2240/10 , F05D2240/126 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle baffle includes a plurality of apertures inclined through a shell for discharging a coolant tangentially therefrom. The baffle is disposed inside a nozzle vane and the tangentially discharged coolant flows generally parallel along the inner surface of the vane for convection cooling thereof.
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5.发明授权Cooling air ducting system in the high pressure turbine section of a gas turbine engine 有权燃气涡轮发动机的高压涡轮部分中的冷却空气管道系统公开(公告)号：US06551056B2
公开(公告)日：2003-04-22
申请号：US09741847
申请日：2000-12-22
申请人： Guido Dr. Rau
发明人： Guido Dr. Rau
IPC分类号： F01D906
摘要： This invention relates to a cooling air ducting system in the high-pressure turbine section of a gas turbine engine, in which a portion of the air flow which exits from the compressor section of the engine and bypasses the combustion chamber of the gas turbine is ducted via a first pre-swirl system provided in a diaphragm into a pre-swirl chamber arranged upstream of the first stage turbine rotor disk and is fed from this pre-swirl chamber, in particular, to the air-cooled blades of this rotor disk for cooling purposes, and in which another portion of this air flow is applied to the face of the first stage turbine rotor disk via a second air transfer system which, when viewed in the radial direction, is arranged further inward than the first pre-swirl system. According to this invention, the second air transfer system is again provided as a pre-swirl system connecting to the pre-swirl chamber. Preferably, a sealing system is provided between a section of the diaphragm which confines the pre-swirl chamber and the turbine shaft section adjacent to this diaphragm section, this sealing system being less permissive of leak air than the labyrinth-type seals commonly used in this application.
摘要翻译： 本发明涉及一种在燃气轮机发动机的高压涡轮机部分中的冷却空气管道系统，其中从发动机的压缩机部分排出并绕过燃气轮机的燃烧室的空气流的一部分被导管 通过设置在隔膜中的第一预旋转系统设置在设置在第一级涡轮转子盘的上游的预涡流室中，并且从该预涡流室特别地供给到该转子盘的风冷叶片， 冷却目的，并且其中该空气流的另一部分经由第二空气传送系统施加到第一级涡轮机转子盘的表面，当从径向方向观察时，该第二空气传送系统比第一预旋转系统更靠内 。 根据本发明，第二空气传送系统再次设置为连接到预涡流室的预旋转系统。 优选地，密封系统设置在膜片的限定预涡旋室和与该隔膜部分相邻的涡轮机轴部分的部分之间，该密封系统比通常在其中常用的迷宫式密封件更不容易泄漏空气 应用。
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公开(公告)号：US06761529B2
公开(公告)日：2004-07-13
申请号：US10202654
申请日：2002-07-25
IPC分类号： F01D906
CPC分类号： F01D5/187 , F01D9/041 , F05D2240/81 , F05D2260/201
摘要： A collision plate having plural small holes is provided at an interval from a bottom surface of an inner shroud to form a chamber and guides cooling air from the small holes into the chamber. A leading edge flow path is provided at a leading edge side along a width direction and introduces the cooling air. A side flow path is provided along both sides of the inner shroud and guides the cooling air to a trailing edge side. A header is formed along the width direction near the trailing edge and guides the cooling air from the side flow path. Plural trailing edge flow paths are formed at the trailing edge side at intervals along a width direction, in which one end of each flow path is connected to the header and the other end is open at the trailing edge, and the cooling air in the header is ejected from the trailing edge.
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公开(公告)号：US06652220B2
公开(公告)日：2003-11-25
申请号：US09998947
申请日：2001-11-15
IPC分类号： F01D906
CPC分类号： F01D25/12 , F01D5/189 , F01D9/02 , F05D2260/201 , Y02T50/676
摘要： A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.
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8.发明授权Method for controlling coolant flow in airfoil, flow control structure and airfoil incorporating the same 有权用于控制翼型件中的冷却剂流动的方法，流量控制结构和包括其的翼型件公开(公告)号：US06589010B2
公开(公告)日：2003-07-08
申请号：US09682373
申请日：2001-08-27
IPC分类号： F01D906
CPC分类号： F01D5/187 , F05D2240/81
摘要： A coolant flow control structure is provided to channel cooling media flow to the fillet region defined at the transition between the wall of a nozzle vane and a wall of a nozzle segment, for cooling the fillet region. In an exemplary embodiment, the flow control structure defines a gap with the fillet region to achieve the required heat transfer coefficients in this region to meet part life requirements.
摘要翻译： 提供冷却剂流动控制结构以将冷却介质流引导到限定在喷嘴叶片的壁和喷嘴段的壁之间的过渡处的圆角区域，以冷却圆角区域。 在示例性实施例中，流动控制结构限定了与圆角区域的间隙，以在该区域中实现所需的传热系数以满足部件寿命要求。
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公开(公告)号：US06565311B2
公开(公告)日：2003-05-20
申请号：US09988720
申请日：2001-11-20
IPC分类号： F01D906
摘要： Gas turbine steam passage seal structure between a blade ring and a stationary blade absorbs thermal deformation to prevent occurrence of minute gaps to thereby reduce leakage of steam as cooling medium. A blade ring steam passage hole, provided in the blade ring (10), has a stepped portion formed in a middle portion thereof. A stationary blade steam passage hole, provided in the stationary blade (50) so as to oppose the blade ring steam passage hole, has a stepped portion formed in an outer peripheral portion thereof. A cooling steam supply passage connection portion is constructed comprising a seal pipe (25) provided between the blade ring and stationary blade steam passage holes so as to communicate them with each other and a seal urging guide device (44, 47) provided at each of the stepped portions of the blade ring and stationary blade steam passage holes so as to effect a seal while fixedly supporting the seal pipe (25). Leakage of the steam is reduced, temperature lowering of combustion gas is prevented, drive force of a steam turbine is increased and the entire thermal efficiency of the combined cycle power plant can be enhanced.
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10.发明授权公开(公告)号：US06398485B1
公开(公告)日：2002-06-04
申请号：US09579520
申请日：2000-05-26
申请人： Franco Frosini , Piero Jacopetti
发明人： Franco Frosini , Piero Jacopetti
IPC分类号： F01D906
摘要： A device for positioning of nozzles of a stator stage and for cooling of rotor discs in gas turbines, of the type including nozzle segments consisting of several airfoils. Each nozzle segment is connected at its top to an outer ring to define a chamber containing cooling air and is positioned at its base on an inner ring. The nozzle segments form a circumferential array about the axis of the gas turbine. In each airfoil of the nozzle segment, there is provided at least one tube, which is inserted in a corresponding duct inside the airfoil for delivering cooling air to the first and second stage discs.
摘要翻译： 一种用于定位定子级的喷嘴并用于冷却燃气轮机中的转子盘的装置，其包括由几个翼型件组成的喷嘴段。 每个喷嘴段在其顶部连接到外环以限定包含冷却空气的室并且位于其内部的内环上。 喷嘴段围绕燃气轮机的轴线形成圆周阵列。 在喷嘴段的每个翼型件中，设置有至少一个管，该管被插入翼型件内的相应的管道中，用于将冷却空气输送到第一和第二台盘。
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