公开(公告)号：US06547525B2

公开(公告)日：2003-04-15

申请号：US09984204

申请日：2001-10-29

申请人： Hartmut Haehnle ,  Ibrahim El-Nashar ,  Rudolf Kellerer ,  Beat Von Arx

发明人： Hartmut Haehnle ,  Ibrahim El-Nashar ,  Rudolf Kellerer ,  Beat Von Arx

IPC分类号： F01D508

CPC分类号： F01D5/187 ,  B22C9/10 ,  B22C9/24 ,  Y10T29/49341

摘要： A cooled component, such as a turbine blade for gas turbines is provided, having efficient internal cooling, with an interior cooling passageway having a round cross-section. A row of feeding holes for the coolant are arranged spaced from each other in the direction of the longitudinal axis of the cooling passageway and originating from a common coolant channel. Each of the feeding holes intersects the cooling passageway tangentially. The ease of manufacturing the cooling component is improved in that the majority of the feeding holes have a hole diameter that is smaller than half of the hydraulic diameter of the cooling passageway, and selected feeding holes have a hole diameter that is greater than half of the hydraulic diameter of the cooling channel.

公开(公告)号：US06422818B2

公开(公告)日：2002-07-23

申请号：US09769749

申请日：2001-01-26

申请人： Thomas Charles Mashey

发明人： Thomas Charles Mashey

IPC分类号： F01D508

CPC分类号： C23C28/321 ,  C23C28/34 ,  C23C28/347 ,  F01D5/084 ,  F01D9/06 ,  F01D25/18 ,  F05C2201/0463 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/509 ,  F05D2300/611 ,  F16L58/08 ,  F16L58/14

摘要： Cooling steam delivery tubes extend axially along the outer rim of a gas turbine rotor for supplying cooling steam to and returning spent cooling steam from the turbine buckets. Because of the high friction forces at the interface of the tubes and supporting elements due to rotor rotation, a low coefficient of friction coating is provided at the interface of the tubes and support elements. On each surface, a first coating of a cobalt-based alloy is sprayed onto the surface at high temperature. A portion of the first coating is machined off to provide a smooth, hard surface. A second ceramic-based solid film lubricant is sprayed onto the first coating. By reducing the resistance to axial displacement of the tubes relative to the supporting elements due to thermal expansion, the service life of the tubes is substantially extended.

摘要翻译： 冷却蒸汽输送管沿着燃气涡轮机转子的外缘轴向延伸，用于将冷却蒸汽供给并从涡轮机叶返回废冷却蒸汽。 由于由于转子旋转而在管和支撑元件的界面处的高摩擦力，在管和支撑元件的界面处提供了低摩擦系数涂层。 在每个表面上，钴基合金的第一涂层在高温下喷涂到表面上。 第一涂层的一部分被加工以提供光滑的硬表面。 将第二陶瓷基固体膜润滑剂喷涂到第一涂层上。 通过由于热膨胀减小管相对于支撑元件的轴向位移的阻力，管的使用寿命显着延长。

公开(公告)号：US06416283B1

公开(公告)日：2002-07-09

申请号：US09688579

申请日：2000-10-16

申请人： Robert A. Johnson ,  Ching-Pang Lee ,  Bin Wei ,  Hsin-Pang Wang

发明人： Robert A. Johnson ,  Ching-Pang Lee ,  Bin Wei ,  Hsin-Pang Wang

IPC分类号： F01D508

CPC分类号： B23H1/04 ,  B23H9/10 ,  B23H9/14 ,  F05B2260/222

摘要： An electrode having a dielectric coating is patterned to provide axially spaced rows of insulating material on the external surface of the electrode with one or more gaps in the insulating material of each row. The electrode is placed in a preformed hole of a turbine bucket and an electrolyte is provided for flow between the electrode and the walls of the hole. Upon application of an electrical current, portions of the material of the interior wall surface directly opposite the non-insulated portions of the electrode are dissolved, forming grooves. The insulated portions of the electrode leave axially spaced rows of projections extending toward the axis of the hole. The gaps in the rows or projections are axially misaligned. The projections form turbulators in the cooling flow passages of the bucket, enhancing the heat transfer coefficient.

摘要翻译： 具有电介质涂层的电极被图案化以在电极的外表面上提供轴向隔开的一排绝缘材料，其中每行的绝缘材料中具有一个或多个间隙。 将电极放置在涡轮机桶的预制孔中，并且提供电解质以在电极和孔的壁之间流动。 在施加电流时，直接与电极的非绝缘部分相对的内壁表面的材料部分被溶解，形成凹槽。 电极的绝缘部分沿着孔的轴线离开轴向间隔开的一列突起。 行或突起中的间隙轴向不对准。 这些突起在铲斗的冷却流动通道中形成涡轮，提高了传热系数。

公开(公告)号：US06267556B1

公开(公告)日：2001-07-31

申请号：US09294897

申请日：1999-04-20

申请人： Masataka Kikuchi ,  Toru Takahashi

发明人： Masataka Kikuchi ,  Toru Takahashi

IPC分类号： F01D508

CPC分类号： F01D25/243 ,  F01D25/265 ,  F05B2260/301 ,  F05D2240/14

摘要： A steam turbine includes a turbine casing, in which a turbine rotor is accommodated so as to extend along a direction of flow of steam, and a plurality of turbine pressure sections are mounted to the turbine rotor, which includes, in combination, at least two or more of a turbine high pressure portion, a turbine intermediate pressure portion and a turbine low pressure portion. The turbine casing is divided into two casing sections, each of the divided turbine casing sections being further divided into a turbine casing upper half and a turbine casing lower half, and the turbine casing lower halves of the divided turbine casing sections being connected to each other by a fastening member such as stud bolt inserted from a side of the turbine low pressure portion.

摘要翻译： 蒸汽涡轮机包括涡轮机壳体，涡轮机转子容纳在涡轮机壳体中，以便沿着蒸汽流动方向延伸，并且多个涡轮压力部分安装到涡轮转子，其组合包括至少两个 涡轮机高压部分，涡轮机中间压力部分和涡轮低压部分。 涡轮机壳体分为两个壳体部分，每个分离的涡轮机壳体部分进一步分为涡轮壳体上半部和涡轮机壳体下半部分，涡轮机壳体的下半部分彼此连接 通过诸如从涡轮机低压部分的侧面插入的双头螺栓的紧固构件。

公开(公告)号：US06267553B1

公开(公告)日：2001-07-31

申请号：US09586549

申请日：2000-05-31

申请人： Joseph C. Burge

发明人： Joseph C. Burge

IPC分类号： F01D508

CPC分类号： F01D5/088 ,  F01D5/06 ,  Y02T50/671 ,  Y02T50/676

摘要： An improved spool for a compressor of a gas turbine engine comprising spacer disks disposed between adjacent rotor disks, and a plurality of hollow tie rods that extend through the rotor disks and the spacer disks. The tie rods are tensionable to provide axial preload between the disks, and also conduct active air for thermally conditioning spool components. The spacer disks have an outer portion with a catenary shape that extends between the peripheral rims of the adjacent rotor disks. Sealing teeth located on the outer portion are preferably radially aligned with a web portion that extends radially inward from a center region on the outer portion. Each tie rod has at least one aperture through its wall for transmitting active air. In one embodiment, active air is injected through apertures in the forward stub shaft of the spool and is urged into at least one space between a rotor disk and a spacer disk, then into, along, and out of the hollow tie rods. In another embodiment active air is injected into open forward ends of the tie rods and subsequently dispersed through apertures in the tie rods. The last stage of the compressor includes a pair of mating forward and aft rotor disks with a cavity formed between the disks. A portion of the active air discharged from the tie rods is circulated in the cavity and into the hollow blades which are integral with the rotor disks. A compressor discharge pressure seal extends axially to the last stage aft rotor disk. The seal has teeth which are oriented generally axially, and preferably have a fishmouth configuration.

摘要翻译： 一种用于燃气涡轮发动机的压缩机的改进的阀芯，包括设置在相邻的转子盘之间的间隔盘，以及延伸穿过转子盘和间隔盘的多个空心拉杆。 拉杆可张紧以在盘之间提供轴向预载，并且还引导主动空气用于热调节卷筒部件。 间隔盘具有在相邻的转子盘的周缘之间延伸的悬链形状的外部部分。 位于外侧部分的密封齿优选地与从外侧部分的中心区域径向向内延伸的腹板部径向对准。 每个拉杆具有穿过其壁的至少一个孔，用于传递主动空气。 在一个实施例中，主动空气通过线轴的前短轴中的孔注入，并被推入转子盘和间隔盘之间的至少一个空间中，然后进入，沿着和离开空心拉杆。 在另一个实施例中，主动空气被注入到拉杆的开放的前端中，并随后通过拉杆中的孔分散。 压缩机的最后阶段包括一对配合的前后转子盘，在盘之间形成有空腔。 从拉杆排出的一部分活性空气在空腔中循环到与转子盘一体的中空叶片中。 压缩机排出压力密封件轴向延伸到转子盘的最后一级。 密封件具有大致轴向定向的齿，并且优选地具有鱼嘴构型。

公开(公告)号：US06220817B1

公开(公告)日：2001-04-24

申请号：US08971305

申请日：1997-11-17

申请人： George A. Durgin ,  Ching-Pang Lee

发明人： George A. Durgin ,  Ching-Pang Lee

IPC分类号： F01D508

CPC分类号： F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

摘要： A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits having outer and inner serpentine portions, respectively, in different longitudinal tiers with the outer serpentine position being disposed longitudinally above the inner tier serpentine position for differentially longitudinally cooling the airfoil. The outer and inner serpentine portions include outer and inner exits and entrances wherein the outer and inner exits are positioned aft of the outer and inner entrances, respectively, so as to have a chordal flow direction aftwards from the leading edge to the trailing edge within the serpentine portions.

摘要翻译： 涡轮机翼片包括多个内部肋条，其限定至少两个独立的蛇形冷却回路，分别在不同的纵向层中具有外部和内部蛇形部分，其中外部蛇形位置纵向设置在内部蛇形位置上方，用于差异地纵向冷却翼型件 。 外部和内部蛇形部分包括外部和外部出口和入口，其中外部出口和内部出口分别位于外部入口和内部入口的后方，以便在内部出口和内部出口之间具有从前缘到后缘的弦向流动方向 蛇纹石部分。

公开(公告)号：US06190128B1

公开(公告)日：2001-02-20

申请号：US09230942

申请日：1999-02-04

申请人： Hiroki Fukuno ,  Yasuoki Tomita ,  Shigeyuki Maeda ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga

发明人： Hiroki Fukuno ,  Yasuoki Tomita ,  Shigeyuki Maeda ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga

IPC分类号： F01D508

CPC分类号： F01D5/147 ,  F01D5/141 ,  F01D5/18 ,  F01D5/187 ,  F01D5/28 ,  F05D2240/80

摘要： A cooled moving blade for a gas turbine which has a blade profile capable of more effectively reducing thermal stress in a blade base portion and, thus, preventing cracks from occurring. A moving blade (1) is fixedly secured to a platform (2). On the other hand, a cooling air passage (3) is formed in a serpentine pattern inside of the blade for cooling with cooling air. The moving blade (1) has a base portion of a profile formed by an elliptically curved surface (11) and a rectilinear surface portion (12), wherein the rectilinear surface portion (12) is provided at a hub portion of the blade where thermal stress is large. The cross-sectional area of the blade is increased by providing the rectilinear surface portion (12) The heat capacity is increased, compared with the conventional blade, due to the increased cross-sectional area of the blade. This, in turn, results in a decrease of the temperature difference due to the thermal stress. Thus, the thermal stress can be suppressed more effectively than with the conventional blade.

摘要翻译： 一种用于燃气轮机的冷却的移动叶片，其具有能够更有效地降低叶片基部中的热应力并因此防止裂纹发生的叶片轮廓。 活动叶片（1）固定地固定到平台（2）上。 另一方面，冷却空气通路（3）形成为叶片内的蛇形图案，用冷却空气冷却。 活动叶片（1）具有由椭圆曲面（11）和直线表面部分（12）形成的轮廓的基部，其中直线表面部分（12）设置在叶片的毂部，其中热 压力很大 通过提供直线表面部分（12）来提高叶片的横截面面积。与常规叶片相比，由于叶片的横截面面积增加，热容量增加。 这又导致由于热应力引起的温度差的降低。 因此，与常规叶片相比，可以更有效地抑制热应力。

公开(公告)号：US06832893B2

公开(公告)日：2004-12-21

申请号：US10278899

申请日：2002-10-24

申请人： Andre Chevrefils ,  Que Dan Pham

发明人： Andre Chevrefils ,  Que Dan Pham

IPC分类号： F01D508

CPC分类号： F01D5/081 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/22141

摘要： A passively cooled blade platform for a gas turbine rotor adapted for rotation about an axis within a stationary coolant fluid. The platform has a radially outer surface defining an annular gas path, a radially inner surface in flow communication with the coolant fluid, a leading edge, and a trailing edge. The inner surface includes at least one cooling flow channel in the inner surface. Each channel has a flow path from a channel inlet to a channel outlet, preferably with a tangential component at the inlet opposite to the direction of rotation and an axial component at the outlet. The flow channels are defined by ribs or pedestals extending radially inwardly from the platform inner surface to direct cooling fluid flow and create turbulence to dissipate heat from the platform on exposure to cooling fluid flow.

摘要翻译： 用于燃气轮机转子的被动冷却的叶片平台，其适于围绕固定的冷却剂流体内的轴线旋转。 平台具有限定环形气体路径的径向外表面，与冷却剂流体，前缘和后缘流动连通的径向内表面。 内表面包括在内表面中的至少一个冷却流道。 每个通道具有从通道入口到通道出口的流动路径，优选地在与入口方向相反的入口处的切向部件和出口处的轴向部件。 流动通道由从平台内表面径向向内延伸的肋或基座限定，以引导冷却流体流动并且在暴露于冷却流体流动时产生湍流以从平台散发热量。

公开(公告)号：US06682304B2

公开(公告)日：2004-01-27

申请号：US09996684

申请日：2001-11-30

申请人： Alexander Beeck ,  Reinhard Fried ,  Markus Oehl

发明人： Alexander Beeck ,  Reinhard Fried ,  Markus Oehl

IPC分类号： F01D508

CPC分类号： F01D5/081 ,  F01D5/187 ,  F01D5/22 ,  F01D5/225 ,  F01D25/12 ,  F05D2240/81 ,  F05D2250/191

摘要： A cooled gas turbine blade with a shroud in which a cooling channel system is provided, which is closed off radially to the gas turbine blade with a cover plate is characterized in that the cover plate has a circumferential edge, along the entire extension of which the cover plate enters into a continuous shape-mated connection or a plurality of locally limited shape-mated connections with the shroud.

摘要翻译： 一种具有护罩的冷却式燃气轮机叶片，其中设有冷却通道系统，该冷却通道系统通过盖板径向封闭到燃气轮机叶片，其特征在于，所述盖板具有周向边缘，沿其整个延伸部分 盖板进入与护罩的连续形状配合连接或多个局部限定的形状配合连接。

公开(公告)号：US06464461B2

公开(公告)日：2002-10-15

申请号：US09731982

申请日：2000-12-08

申请人： Ian David Wilson ,  Kevin Joseph Barb ,  Ming Cheng Li ,  Susan Marie Hyde ,  Thomas Charles Mashey ,  Ronald Richard Wesorick ,  Christopher Charles Glynn ,  Martin C. Hemsworth

发明人： Ian David Wilson ,  Kevin Joseph Barb ,  Ming Cheng Li ,  Susan Marie Hyde ,  Thomas Charles Mashey ,  Ronald Richard Wesorick ,  Christopher Charles Glynn ,  Martin C. Hemsworth

IPC分类号： F01D508

CPC分类号： F01D5/085 ,  F02C7/16 ,  F05D2260/2322 ,  Y02T50/676

摘要： The steam cooling circuit for a gas turbine includes a bore tube assembly supplying steam to circumferentially spaced radial tubes coupled to supply elbows for transitioning the radial steam flow in an axial direction along steam supply tubes adjacent the rim of the rotor. The supply tubes supply steam to circumferentially spaced manifold segments located on the aft side of the 1-2 spacer for supplying steam to the buckets of the first and second stages. Spent return steam from these buckets flows to a plurality of circumferentially spaced return manifold segments disposed on the forward face of the 1-2 spacer. Crossover tubes couple the steam supply from the steam supply manifold segments through the 1-2 spacer to the buckets of the first stage. Crossover tubes through the 1-2 spacer also return steam from the buckets of the second stage to the return manifold segments. Axially extending return tubes convey spent cooling steam from the return manifold segments to radial tubes via return elbows.

摘要翻译： 用于燃气涡轮机的蒸汽冷却回路包括孔管组件，其将周向间隔开的径向管供给蒸汽，所述径向管连接到供应弯头，以沿着与沿转子边缘的蒸汽供应管沿轴向方向转换径向蒸汽流。 供应管将位于1-2间隔物的后侧的周向隔开的歧管段供应蒸汽，以将蒸汽供应到第一和第二级的桶。 来自这些铲斗的废水返回蒸汽流向设置在1-2间隔物的前表面上的多个周向间隔开的返回歧管段。 交叉管将来自蒸汽供应歧管段的蒸汽供应通过1-2间隔件连接到第一级的桶。 通过1-2间隔物的交叉管还将蒸汽从第二级的桶返回到回流歧管段。 轴向延伸的回流管通过返回弯头将废冷却蒸汽从返回歧管段传送到径向管。