公开(公告)号：US06688847B2

公开(公告)日：2004-02-10

申请号：US09942619

申请日：2001-08-31

申请人： Takeaki Oya ,  Kazuharu Hirokawa ,  Tadateru Tanioka ,  Tanehiro Shinohara ,  Katsunori Tanaka ,  Kazuo Uematsu

发明人： Takeaki Oya ,  Kazuharu Hirokawa ,  Tadateru Tanioka ,  Tanehiro Shinohara ,  Katsunori Tanaka ,  Kazuo Uematsu

IPC分类号： F01D508

CPC分类号： F01D5/085 ,  F01D5/08 ,  F01D25/125 ,  F05D2240/61 ,  F05D2260/205 ,  F05D2260/2322

摘要： A shaft structure of a rotor tail end of a gas turbine in which a steam passage for supplying and recovering a steam for cooling rotor blades of the gas turbine extends along a center axis of the rotor assembly of the gas turbine is provided, wherein a center hole of the rotor tail end coaxial to the center axis of the steam passage is formed in the rotor tail end. Provision is also made of a thermal sleeve between the steam passage and the inner surface of the center hole of the rotor tail end, so that a thermal insulation gas layer is formed between the inner surface of the center hole of the rotor tail end and the thermal sleeve. The thermal insulation gas layer is isolated gas-tightly and liquid-tightly from the outside.

摘要翻译： 提供一种燃气轮机的转子尾端的轴结构，其中用于供应和回收用于冷却燃气涡轮机的转子叶片的蒸汽的蒸汽通道沿着燃气轮机的转子组件的中心轴延伸，其中中心 在转子尾端形成有与蒸汽通道的中心轴同轴的转子尾端的孔。 在蒸汽通道和转子尾端的中心孔的内表面之间还设置有热套筒，使得在转子尾端的中心孔的内表面和 热套。 绝热气体层从外部气密地液密隔离。

公开(公告)号：US06572334B2

公开(公告)日：2003-06-03

申请号：US09996692

申请日：2001-11-30

申请人： Daniel Hediger ,  Ernoe Stefan

发明人： Daniel Hediger ,  Ernoe Stefan

IPC分类号： F01D508

CPC分类号： H02K1/32

摘要： The cap plate has an axially recessed region with a shoulder. The gas guiding ring half shells have a respective projecting rib. A retaining ring consisting of two retaining ring halves abuts with its first leg in the shoulder and is connected by means of fillister head screws to the cap plate. The gas guiding ring half shells are positioned with respect to the cap plate with clearance fit in the radial and axial direction. The ribs have a spacing in the peripheral direction at the separation place of the gas guiding ring half shells in order to form gaps. At the same location, the first leg of the retaining ring halves is interrupted for the formation of recesses aligned with the gaps. Fixing wedges are inserted in the region of the gaps and of the recesses and are screwed to the cap plate. These fixing wedges transfer the tangential forces from the gas guiding ring half shells to the retaining ring halves.

摘要翻译： 盖板具有带肩部的轴向凹陷区域。 气体引导环半壳具有相应的突出肋。 由两个保持环半部组成的保持环与其第一腿邻接在肩部中，并通过吸头头螺钉连接到盖板。 导气环半壳相对于盖板以径向和轴向间隙配合定位。 这些肋在气体导向环半壳的分离位置处在周向方向上具有间隔，以形成间隙。 在相同的位置，保持环半部的第一腿被中断以形成与间隙对准的凹部。 固定楔被插入在间隙和凹部的区域中，并被拧到盖板上。 这些固定楔将切向力从气体引导环半壳传递到保持环半部。

公开(公告)号：US06514041B1

公开(公告)日：2003-02-04

申请号：US09949636

申请日：2001-09-12

申请人： Alfred Paul Matheny ,  Alexander Beeck

发明人： Alfred Paul Matheny ,  Alexander Beeck

IPC分类号： F01D508

CPC分类号： F01D25/246 ,  F01D11/18

摘要： A thermal turbo machine is provided for the attachment of guide vanes on its stationary housing with guide vane carriers with a guide vane platform, from which braces extend towards a band that is suspended in a recess in the stationary housing. In particular, part of the axially adjoining heat shield segments form part of the guide vane platform, and the braces are arranged in a V shape. The braces and the guide vane platform furthermore include a first material, and the band of a second material, whereby the first material has a higher coefficient of expansion than the second material. The guide vane carrier according to the invention has the advantage that the radial blade clearance for the guide vanes and at the same time the radial blade clearance for the rotating blades is minimized for different operating conditions of the turbo machine.

摘要翻译： 提供了一种热涡轮机，用于将导向叶片安装在其固定壳体上，该导向叶片载体具有导向叶片平台，该支架从该导向叶片承载件延伸到悬挂在固定壳体中的凹槽中的带状物上。 特别地，轴向相邻的隔热片的一部分形成导叶平台的一部分，并且支架被布置成V形。 支架和导向叶片平台还包括第一材料和第二材料的带，由此第一材料具有比第二材料更高的膨胀系数。 根据本发明的导叶载体的优点在于，对于涡轮机的不同操作条件，用于导向叶片的径向叶片间隙和同时用于旋转叶片的径向叶片间隙最小化。

公开(公告)号：US06471478B1

公开(公告)日：2002-10-29

申请号：US09694756

申请日：2000-10-24

申请人： Thomas Charles Mashey

发明人： Thomas Charles Mashey

IPC分类号： F01D508

CPC分类号： F01D5/08 ,  F01D5/084 ,  F01D11/005 ,  Y02T50/676 ,  Y10S285/917

摘要： An axial seal assembly is provided at the interface between adjacent wheels and spacers of a gas turbine rotor and disposed about tubes passing through openings in the rotor adjacent the rotor rim and carrying a thermal medium. Each seal assembly includes a support bushing for supporting a land of the thermal medium carrying tube, an axially registering seat bushing disposed in the opposed opening and a frustoconical seal between the seal bushing and seat. The seal bushing includes a radial flange having an annular recess for retaining the outer diameter edge of the seal, while the seat bushing has an axially facing annular surface forming a seat for engagement by the inner diameter edge of the seal.

摘要翻译： 轴向密封组件设置在燃气轮机转子的相邻车轮和间隔件之间的界面处，并且围绕与转子轮缘相邻的转子周围的管道设置，并承载热介质。 每个密封组件包括支撑衬套，用于支撑热介质承载管的平台，设置在相对的开口中的轴向对齐的座套管和在密封衬套和座之间的截头圆锥形密封。 密封衬套包括径向凸缘，其具有用于保持密封件的外径边缘的环形凹部，同时座套管具有轴向面向的环形表面，该环形表面形成用于由密封件的内径边缘接合的阀座。

公开(公告)号：US06361277B1

公开(公告)日：2002-03-26

申请号：US09490625

申请日：2000-01-24

申请人： David E. Bulman ,  Kenneth E. Seitzer ,  Craig P. Burns ,  Jeffrey D. Clements

发明人： David E. Bulman ,  Kenneth E. Seitzer ,  Craig P. Burns ,  Jeffrey D. Clements

IPC分类号： F01D508

CPC分类号： F04D29/582 ,  F01D5/082 ,  F01D5/085 ,  F04D29/321 ,  Y02T50/676

摘要： A gas turbine engine includes a compressor rotor assembly which directs air at a sufficent pressure and temperature to a compressor rotor bore. The compressor assembly includes a compressor including a plurality of rotors joined with a plurality of couplings. Each of the rotors includes a radially outer rim, a radially inner hub, and a web extending therebetween. The web includes a flange including a plurality of slots which define a plurality of radial vanes that are airfoil-shaped. The vanes effectively deswirl bleed air and re-direct the airflow to a compressor bore.

摘要翻译： 燃气涡轮发动机包括压缩机转子组件，其将足够的压力和温度的空气引导到压缩机转子孔。 压缩机组件包括压缩机，该压缩机包括与多个联接器连接的多个转子。 每个转子包括径向外缘，径向内轮毂和在其间延伸的腹板。 腹板包括凸缘，其包括限定多个翼型的径向叶片的多个狭槽。 叶片有效地消除放气并将气流重新引导至压缩机孔。

公开(公告)号：US06331097B1

公开(公告)日：2001-12-18

申请号：US09410239

申请日：1999-09-30

申请人： Richard W. Jendrix

发明人： Richard W. Jendrix

IPC分类号： F01D508

CPC分类号： F01D5/081 ,  F01D5/3015 ,  F05D2260/607 ,  Y02T50/676

摘要： A turbine rotor for a gas turbine engine includes a rotor disk having a plurality of circumferentially alternating dovetail slots and disk posts and a plurality of blades disposed in the dovetail slots. A cooling air plenum is defined in the portion of each dovetail slot located radially inward of the corresponding blade. Air from the plenums is directed through slots formed in axial surfaces of the blades or disk posts into an adjacent wheel cavity, thereby purging the wheel cavity.

摘要翻译： 用于燃气涡轮发动机的涡轮转子包括具有多个周向交替的燕尾槽和盘柱的转子盘和设置在燕尾槽中的多个叶片。 在位于相应叶片的径向内侧的每个燕尾槽的部分中限定有冷却空气增压室。 来自气室的空气被引导通过形成在叶片或盘柱的轴向表面中的槽到相邻的轮腔中，从而清洗轮腔。

公开(公告)号：US06305903B1

公开(公告)日：2001-10-23

申请号：US09379465

申请日：1999-08-24

申请人： Klaus Semmler ,  Bernhard Weigand

发明人： Klaus Semmler ,  Bernhard Weigand

IPC分类号： F01D508

CPC分类号： F01D5/187 ,  F05D2260/221

摘要： A cooled vane for a gas turbine or similar device including a vane blade constructed of a suction side wall and a pressure side wall that are connected via a leading edge and a trailing edge with each other, which has an essentially radially extending cavity through which a cooling medium is capable of flowing. The vane blade has multiple cooling channels that, starting from the cavity, extend through a vane section adjoining the trailing edge and formed by sections of the suction side wall and the pressure side wall, and end at the trailing edge. A first row of cooling channels is associated with the suction side (SS) of the vane blade, and a second row of cooling channels is associated with the pressure side (DS) of the vane blade. The cooled vane has improved cooling efficiency and can be produced entirely with a casting process while complying with basic geometric conditions.

摘要翻译： 一种用于燃气轮机或类似装置的冷却叶片，包括由吸入侧壁和压力侧壁构成的叶片叶片，该叶片叶片经由前缘和后缘彼此连接，所述侧壁具有基本上径向延伸的空腔， 冷却介质能够流动。 叶片叶片具有多个冷却通道，其从腔体开始延伸通过与后缘相邻的叶片部分并且由吸力侧壁和压力侧壁的部分形成并且在后缘处结束。 第一排冷却通道与叶片的吸入侧（SS）相关联，第二排冷却通道与叶片的压力侧（DS）相关联。 冷却的叶片具有提高的冷却效率，并且可以在符合基本几何条件的情况下通过铸造工艺完全制造。

公开(公告)号：US06276896B1

公开(公告)日：2001-08-21

申请号：US09626289

申请日：2000-07-25

申请人： Joseph C. Burge ,  Norman Paul Poire

发明人： Joseph C. Burge ,  Norman Paul Poire

IPC分类号： F01D508

CPC分类号： F01D5/046 ,  F01D5/048 ,  F04D29/284 ,  F04D29/584 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/673

摘要： An apparatus and method for cooling an impeller for an axi-centrifugal compressor of a gas turbine engine. A curvic coupling joint is used between the aft end of the impeller and the turbine shaft. A generally annular disk-shaped shield structure is attached to the aft face of the impeller and extends from the impeller rim to the turbine shaft just aft of the curvic coupling. The shield structure is offset from the aft face of the impeller thereby forming a cavity therebetween. The shield structure has a plurality of circumferentially space apertures through which cooling air passes to first circulate through the cavity by means of radial vanes to cool the impeller, then exit through the curvic coupling joint. The cooling air is then directed afterward along the turbine shaft to be used to cool high-pressure turbine blades.

摘要翻译： 一种用于冷却燃气轮机的轴离心式压缩机的叶轮的装置和方法。 在叶轮的后端和涡轮轴之间使用弯曲的联接接头。 大致环形的盘形屏蔽结构附接到叶轮的后表面，并且在曲轴联接器的后方从叶轮边缘延伸到涡轮轴。 屏蔽结构从叶轮的后表面偏移，从而在它们之间形成空腔。 屏蔽结构具有多个周向空间孔，冷却空气通过该孔，首先通过径向叶片循环通过空腔，以冷却叶轮，然后通过弯曲的耦合接头离开。 然后冷却空气随后沿着涡轮轴被引导以用于冷却高压涡轮叶片。

公开(公告)号：US06808362B1

公开(公告)日：2004-10-26

申请号：US10204479

申请日：2002-10-31

申请人： Joern-Axel Glahn ,  Armin Heger ,  Joerg Pross

发明人： Joern-Axel Glahn ,  Armin Heger ,  Joerg Pross

IPC分类号： F01D508

CPC分类号： F01D5/087 ,  F04D29/321

摘要： A rotor for a gas turbine is disclosed. The rotor has a plurality of rotor disks arranged one behind the other on a rotor axis. The rotor extends between a compressor part and a turbine part, and has a central bore running between the compressor part and the turbine part. Fluid passages are arranged to conduct cooling air from the compressor part and direct cooling through the central bore and direct cooling air from the turbine part radially outward through the rotor. The rotor disks have fluid cavities that are connected to the central bore by having an outer diameter that is greater than the inside diameter of the central bore. The fluid cavities are subdivided into individual chambers by a plurality of radial ribs.

摘要翻译： 公开了一种用于燃气轮机的转子。 转子具有在转子轴上一个接一个地布置的多个转子盘。 转子在压缩机部件和涡轮机部件之间延伸，并且具有在压缩机部件和涡轮机部件之间延伸的中心孔。 流体通道被布置成从压缩机部分传导冷却空气，并直接通过中心孔进行冷却，并将来自涡轮部分的冷却空气直接通过转子径向向外。 转子盘具有通过具有大于中心孔的内径的外径连接到中心孔的流体腔。 流体腔通过多个径向肋细分成单个腔室。

公开(公告)号：US06755613B1

公开(公告)日：2004-06-29

申请号：US09959974

申请日：2001-11-14

申请人： Friedhelm Schmitz

发明人： Friedhelm Schmitz

IPC分类号： F01D508

CPC分类号： C23C2/12 ,  C23C26/00 ,  F01D5/288 ,  F22B37/04

摘要： A steam turbine component coated with a protective layer can be exposed to hot vapor. The component has a metallic base body, to which the protective layer is bonded by diffusion in order to increase the resistance of the base material to oxidation. The protective layer contains aluminum and has a thickness of less than 50 &mgr;m. The protective coating can be formed by applying an aluminum pigment to the base body and maintaining the component at a predetermined temperature.

摘要翻译： 涂有保护层的汽轮机组件可能暴露于热蒸汽。 该组件具有金属基体，通过扩散将保护层结合到该金属基体上，以增加基底材料对氧化的电阻。 保护层含有铝，厚度小于50μm。 保护涂层可以通过将铝颜料涂覆到基体上并将组分保持在预定温度而形成。