公开(公告)号：US06595749B2

公开(公告)日：2003-07-22

申请号：US09940812

申请日：2001-08-28

Applicant: Ching-Pang Lee ,  Lawrence Joseph Roedl ,  Jonathan James Stow

Inventor： Ching-Pang Lee ,  Lawrence Joseph Roedl ,  Jonathan James Stow

IPC: F01D518

CPC classification number: B23P6/005 ,  B23P6/007 ,  B23P15/04 ,  F01D5/005 ,  F01D5/18 ,  F01D5/20 ,  F05D2230/23 ,  F05D2230/80 ,  F05D2260/201 ,  F05D2260/202 ,  Y10T29/49318 ,  Y10T29/49341

Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip defining a tip shelf, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.

公开(公告)号：US06575703B2

公开(公告)日：2003-06-10

申请号：US09910155

申请日：2001-07-20

Applicant: Peter A. Simeone ,  Gary C. Liotta

Inventor： Peter A. Simeone ,  Gary C. Liotta

IPC: F01D518

CPC classification number: F01D5/066 ,  F01D5/3015 ,  F01D11/006 ,  F05D2260/30

Abstract: An annular disk side plate for a gas turbine engine rotor assembly includes an annular plate hub and an annular plate shaft extension extending axially forwardly from the plate hub. A plate web extends radially outwardly from the plate hub and a plate rim extends radially outwardly from the plate web. In the exemplary embodiments of the invention illustrated herein, the plate rim is canted aftwardly from the plate web. One or more annular sealing ridges extend aftwardly from the plate rim. The side plate further includes an anti-rotation means for preventing rotation of the disk side plate relative to the disk such as a circumferential row of radially extending circumferentially spaced apart tabs. Cooling air apertures or holes extend axially through the plate web. A rotor assembly further includes an annular rotor disk comprising a disk hub and an annular disk shaft extension extending axially forward from the disk hub. A disk web extends radially outwardly from the disk hub, a disk rim extends radially outwardly from the disk web, and the disk rim has a forward facing seal face. Rotor blades are mounted in and extend radially outwardly from the disk rim. The annular disk side plate is mounted on an annular forward facing side of the disk and the plate shaft extension is mounted on the disk shaft extension. A pre-loading means for pre-loading the side plate in compression against disk seals the annular sealing ridges against the seal face by axially securing the plate shaft extension to the disk shaft extension.

Abstract translation: 用于燃气涡轮发动机转子组件的环形盘侧板包括环形板毂和从板毂轴向向前延伸的环形板轴延伸。 板腹板从板毂径向向外延伸，并且板缘从板腹板径向向外延伸。 在本文所示的本发明的示例性实施例中，板缘从板腹板向后倾斜。 一个或多个环形密封脊从板边缘向后延伸。 侧板还包括用于防止盘侧板相对于盘的旋转的防旋转装置，例如周向排的径向延伸的周向间隔开的突片。 冷却空气孔或孔轴向延伸穿过板腹板。 转子组件还包括环形转子盘，其包括盘毂和从盘毂轴向向前延伸的环形盘轴延伸。 盘形盘从盘毂径向向外延伸，盘缘从盘片径向向外延伸，并且盘缘具有向前的密封面。 转子叶片安装在圆盘边缘的径向向外并从盘边缘径向向外延伸。 环形盘侧板安装在盘的环形前方侧，板轴延伸部安装在盘轴延伸部上。 用于预压装载侧板的预加载装置通过将板轴延伸部轴向地固定到盘轴延伸部来密封抵靠密封面的环形密封脊。

公开(公告)号：US06514046B1

公开(公告)日：2003-02-04

申请号：US09677044

申请日：2000-09-29

Applicant: Jay A. Morrison ,  Gary B. Merrill ,  Jay E. Lane ,  Christian X. Campbell ,  Daniel G. Thompson ,  Eric V. Carelli ,  Christine Taut

Inventor： Jay A. Morrison ,  Gary B. Merrill ,  Jay E. Lane ,  Christian X. Campbell ,  Daniel G. Thompson ,  Eric V. Carelli ,  Christine Taut

IPC: F01D518

CPC classification number: F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F01D9/02 ,  F05D2260/201 ,  F05D2300/603 ,  F05D2300/611 ,  F05D2300/612

Abstract: A vane assembly for a turbine assembly includes an inner endcap, an outer endcap, and a body. The body includes a metallic core assembly, a ceramic shell assembly and a support assembly. The metallic core assembly is coupled to the inner and outer endcaps and bears most of the mechanical loads, including aerodynamic loads. The ceramic shell bears substantially all of the thermal stress placed on the vane assembly. The support assembly is disposed between the metallic core assembly and said ceramic shell assembly and is coupled to the metallic core assembly.

Abstract translation: 用于涡轮组件的叶片组件包括内端盖，外端盖和主体。 主体包括金属芯组件，陶瓷壳组件和支撑组件。 金属芯组件联接到内外端盖和承载大部分机械负载，包括空气动力学负载。 陶瓷壳承受放置在叶片组件上的基本上所有的热应力。 支撑组件设置在金属芯组件和所述陶瓷壳组件之间并且联接到金属芯组件。

公开(公告)号：US06481966B2

公开(公告)日：2002-11-19

申请号：US09739282

申请日：2000-12-19

Applicant: Alexander Beeck ,  Jörgen Ferber ,  Christoph Nagler ,  Lothar Schneider ,  Klaus Semmler

Inventor： Alexander Beeck ,  Jörgen Ferber ,  Christoph Nagler ,  Lothar Schneider ,  Klaus Semmler

IPC: F01D518

CPC classification number: B22D11/0405 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/304

Abstract: In a gas-turbine guide element (30) around which a hot air flow (23) flows and which, at least in a trailing edge region (21), in which the air flow (23) separates from the guide element (30), comprises at least two walls (10, 11) arranged essentially in parallel and connected to one another by ribs (16, 17, 20) in such a way as to form internal cooling passages (18, 19, 25, 26, 27), and which is cooled on the inside with cooling medium (28, 29) flowing through the cooling passages (18, 19, 25, 26, 27), the cooling medium discharging from the guide element (30) at the trailing edge (21) essentially parallel to and between the walls (10, 11), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs (24) so as to terminate essentially flush with the trailing edge (21).

Abstract translation: 在热空气流（23）流过的燃气涡轮引导元件（30）中，并且至少在其中气流（23）与引导元件（30）分离的后缘区域（21）中， 至少两个壁（10,11），其基本上平行布置并且通过肋（16,17,20）彼此连接，以形成内部冷却通道（18,19,25,26,27） 并且在流过冷却通道（18,19,25,26,27）的冷却介质（28,29）在内部冷却，冷却介质从后缘（21）处的引导元件（30）排出 ）基本上平行于壁（10,11），并且在其制造方法中，由于至少一些肋布置为扼流肋（24），实现了更容易的再加工和对外来颗粒的较小的敏感性 ），以便基本上与后缘（21）齐平地终止。

公开(公告)号：US06461108B1

公开(公告)日：2002-10-08

申请号：US09818384

申请日：2001-03-27

Applicant: Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

Inventor： Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

IPC: F01D518

CPC classification number: F01D5/182 ,  C23C28/00 ,  F01D5/183 ,  F01D5/20 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49318

Abstract: A cooling system for cooling of the squealer tip surface region of a high pressure turbine blade used in a gas turbine engine and a method for making a system for cooling of the squealer tip surface region of a high pressure turbine blade used in a gas turbine engine. The method comprises the steps of channeling apertures in a tip cap to a diameter of about 0.004″ to about 0.020″ to allow passage of cooling fluid from a cooling fluid source; applying a bond coat of about 0.0005″ to about 0.010″ in thickness to the tip cap such that the bond coat partially fills the channels; applying a porous TBC layer of at least about 0.003″ in thickness to the bond coat, such that the porous TBC fills the channels; applying a dense ceramic TBC layer over the porous layer; and, passing cooling fluid from a cooling fluid source through the channel into the porous TBC. The density of the dense TBC layer can be varied as needed to achieve desired cooling objectives. Because the channel exit is filled with porous TBC material, cooling fluid flows through the porous passageways in the porous TBC layer into the squealer tip. Although the passageways provide a plurality of tortuous routes, the increased density of the TBC in the dense ceramic layer provides a resistance to flow of the cooling fluid and effectively causes the cooling fluid to more efficiently spread through the TBC into the squealer tip before exiting into the gas stream at the outer surface.

Abstract translation: 一种用于冷却燃气涡轮发动机中使用的高压涡轮机叶片的鸣响器尖端表面区域的冷却系统以及用于冷却燃气涡轮发动机中使用的高压涡轮机叶片的鸣叫器尖端表面区域的系统的方法 。 该方法包括以下步骤：将顶盖中的孔引导至约0.004“至约0.020”的直径，以允许冷却流体从冷却流体源通过; 对顶盖施加厚度为约0.0005“至约0.010”的粘结层，使得粘结涂层部分填充通道; 将至少约0.003“的多孔TBC层施加到粘结涂层，使得多孔TBC填充通道; 在多孔层上施加致密的陶瓷TBC层; 并且将来自冷却流体源的冷却流体通过通道进入多孔TBC。 可以根据需要改变致密TBC层的密度以实现期望的冷却目标。 由于通道出口填充有多孔TBC材料，所以冷却流体流过多孔TBC层中的多孔通道进入到尖叫尖端。 尽管通道提供了多条曲折的路径，但是致密陶瓷层中TBC的增加的密度提供了对冷却流体的流动的阻力，并且有效地使冷却流体更有效地通过TBC传播到鸣叫器尖端中，然后退出 在外表面的气流。

公开(公告)号：US06457935B1

公开(公告)日：2002-10-01

申请号：US09883948

申请日：2001-06-20

Applicant: Serge Louis Antunes ,  Eric Stephan Bil ,  Isabelle Monique Marie Bourriaud ,  Maurice Guy Judet

Inventor： Serge Louis Antunes ,  Eric Stephan Bil ,  Isabelle Monique Marie Bourriaud ,  Maurice Guy Judet

IPC: F01D518

CPC classification number: F01D11/008 ,  F05D2240/81

Abstract: A sheet metal sealing sleeve placed under a pair of juxtaposed blade platforms in a turbomachine so as to cover the gap between them is provided with apertures to allow the flow of a ventilating gas to the platforms. The apertures are provided in bosses formed on the sleeve to define chambers between the sleeve and the platforms which provide for greater heat exchange by virtue of the forcible impact of the gas blown through the apertures under the platforms. The sleeve also aids in damping platform vibration.

Abstract translation: 设置在涡轮机中的一对并置的叶片平台下方以覆盖它们之间的间隙的金属片密封套设置有允许通气气体流到平台的孔。 这些孔设置在形成在套筒上的凸台中，以在套筒和平台之间限定腔室，借助于通过平台下方的孔吹出的气体的强力冲击而提供更大的热交换。 套筒也有助于减震平台振动。

公开(公告)号：US06419449B2

公开(公告)日：2002-07-16

申请号：US09750003

申请日：2000-12-29

Applicant: Jörgen Ferber

Inventor： Jörgen Ferber

IPC: F01D518

CPC classification number: F01D5/188

Abstract: Apparatus is disclosed for providing cooling channels in the interior of a gas turbine rotor blade. The cooling channels are formed by metallic inserts which extend from adjacent the root of the blade toward the tip. The inserts are substantially flat and are secured in the interior of the airfoil section by means of rails which engage the longitudinal edges of the inserts and serve as a guide during insertion. The rails are preferable formed integrally with the blade casting.

Abstract translation: 公开了用于在燃气轮机转子叶片的内部提供冷却通道的装置。 冷却通道由金属插件形成，金属插件从刀片的根部朝向尖端延伸。 插入件基本上是平的，并且通过与插入件的纵向边缘接合的轨道固定在翼型部分的内部，并且在插入期间用作引导件。 轨道优选与刀片铸件一体形成。

公开(公告)号：US06364608B1

公开(公告)日：2002-04-02

申请号：US09595868

申请日：2000-06-16

Applicant: Gulcharan S. Brainch ,  Michael J. Danowski ,  Roger D. Wustman ,  Jonathan P. Clarke

Inventor： Gulcharan S. Brainch ,  Michael J. Danowski ,  Roger D. Wustman ,  Jonathan P. Clarke

IPC: F01D518

CPC classification number: F01D5/20 ,  F01D5/288 ,  Y10T29/49336 ,  Y10T29/49982

Abstract: An article comprising an airfoil surface is provided with a thermal insulating outer layer on at least one region, but not all, of the airfoil surface. The region is selected from the airfoil surface which has been observed to experience more strenuous environmental operating conditions during service operation than the airfoil surface outside of the region. In one form, the thermal insulating outer layer is applied to at least one region of each of a plurality of airfoil surfaces. Each airfoil surface is disposed about an axis of rotation with the region of each airfoil surface facing generally outwardly from the axis of rotation and from each other. The airfoil surfaces are rotated about the axis of rotation while a thermal insulating material contacts at least the regions.

Abstract translation: 包括翼型表面的物品在翼型表面的至少一个区域上但不是全部设置有绝热外层。 该区域选自已经被观察到的在翼片表面在使用操作期间比该区域外的翼面表面经历更剧烈的环境操作条件。 在一种形式中，绝热外层被施加到多个翼型表面中的每一个的至少一个区域。 每个翼面表面围绕旋转轴设置，每个翼型表面的区域从旋转轴线大体上相对于彼此面对。 翼型表面围绕旋转轴线旋转，而绝热材料至少接触该区域。

公开(公告)号：US06340284B1

公开(公告)日：2002-01-22

申请号：US09471410

申请日：1999-12-23

Applicant: Alexander Beeck ,  Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand

Inventor： Alexander Beeck ,  Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand

IPC: F01D518

CPC classification number: F01D5/225 ,  F01D5/187 ,  F05D2240/81

Abstract: In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space. The top side of the shroud band is preferable provided with at least two ribs and, which run in parallel and, in interaction with the opposite casing wall, form a cavity, into which the cooling air discharging from the cooling bores flows.

Abstract translation: 在风冷涡轮机叶片中，在叶片尖端处具有横向于叶片的纵向轴线延伸的护罩带元件，多个冷却孔穿过护罩带元件用于冷却，该冷却 孔在入口侧连接到至少一个冷却空气通道，该冷却空气通道穿过涡轮机叶片到达叶片尖端，并且在出口侧打开到围绕涡轮机叶片的外部空间中，由于以下事实实现了改进和确保的冷却： 所述冷却孔在所述护罩带元件中从内到外延伸至少大致平行于所述叶片的运动方向，并且在每种情况下，在所述护罩带元件的外缘的上游开口朝向所述外部开口的表面凹部 空间。 护罩带的顶侧优选设置有至少两个肋，并且平行延伸并且与相对的壳体壁相互作用形成空腔，冷却孔从冷却孔排出的冷却空气流过。

公开(公告)号：US06290463B1

公开(公告)日：2001-09-18

申请号：US09410241

申请日：1999-09-30

Applicant: David G. W. Fargher ,  Ching-Pang Lee

Inventor： David G. W. Fargher ,  Ching-Pang Lee

IPC: F01D518

CPC classification number: F01D5/187 ,  F05D2260/201 ,  Y02T50/676

Abstract: A coolable gas turbine engine airfoil for a gas turbine engine suitable for a blade or vane includes an outer airfoil wall with pressure and suction sides extending chordwise between leading and trailing edges of the airfoil, a leading edge cooling plenum formed between a forward most span rib and the outer wall along the leading edge of the airfoil, and a cooling air channel within the airfoil bounded in part by the forward most rib. A slotted cooling air impingement element is disposed in the span rib for impinging cooling air from the channel on an interior surface of the outer airfoil wall along the leading edge of the airfoil. One embodiment of the slotted cooling air impingement element is a single longitudinally extending slot extending along almost an entire length of the forward most rib and the longitudinally slot preferably includes longitudinally spaced apart rounded ends. In another embodiment of the airfoil, the slotted cooling air impingement element is includes two or more closely spaced apart longitudinally extending slots extending along almost an entire length of the forward most rib and each of the longitudinally extending slots preferably has longitudinally spaced apart rounded ends

Abstract translation: 用于适用于叶片或叶片的燃气涡轮发动机的可冷却燃气涡轮发动机翼型件包括外翼型壁，其具有在翼型的前缘和后缘之间沿弦向延伸的压力和吸力侧;形成在前翼跨肋之间的前缘冷却气室 以及沿着翼型的前缘的外壁，以及在翼型内部由最前肋部分限定的冷却空气通道。 一个开槽的冷却空气冲击元件设置在该跨度肋中，用于沿着该翼型的前缘沿着该外翼型壁的内表面上的通道冲击冷却空气。 开槽的冷却空气冲击元件的一个实施例是沿着最前面的肋的几乎整个长度延伸的单个纵向延伸的狭槽，并且纵向狭槽优选地包括纵向间隔开的圆形端部。 在翼型的另一实施例中，开槽的冷却空气冲击元件包括两个或更多个紧密间隔开的纵向延伸的狭槽，其沿着最前面的肋的几乎整个长度延伸，并且每个纵向延伸的槽优选地具有纵向间隔开的圆形端