公开(公告)号：US08607455B2

公开(公告)日：2013-12-17

申请号：US12596780

申请日：2008-04-10

Applicant: Fathi Ahmad

Inventor： Fathi Ahmad

IPC: B21D53/78 ,  B21K3/04 ,  B23P6/00 ,  F01D5/16 ,  F01D25/06

CPC classification number: F01D5/288 ,  F01D5/16 ,  F01D5/187 ,  F05D2230/10 ,  F05D2230/80 ,  F05D2250/19 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T29/49726

Abstract: A method for producing a coated turbine blade, with which the frequency property thereof can be particularly easily adjusted to the required boundary conditions is provided. Recesses are introduced into a blade tip of the blade leaf of the turbine blade after coating of turbine blade. In one aspect a plurality of bores are made which are distributed along the blade leaf center line.

Abstract translation: 提供一种用于制造涂覆的涡轮叶片的方法，其特征在于能够将其频率特性容易地调整到所需的边界条件。 在涡轮叶片涂覆之后，将凹陷物引入涡轮机叶片叶片的叶片尖端。 在一个方面，制成沿叶片叶中心线分布的多个孔。

公开(公告)号：US20080031724A1

公开(公告)日：2008-02-07

申请号：US11631768

申请日：2005-06-10

Applicant: Harald Hoell ,  Reimar Schaal ,  Werner Setz

Inventor： Harald Hoell ,  Reimar Schaal ,  Werner Setz

IPC: F01D5/06

CPC classification number: F01D5/06 ,  F01D5/02 ,  F05D2230/10 ,  F05D2250/19 ,  F05D2250/29 ,  F05D2250/291 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  Y10T29/49316

Abstract: The invention relates to a rotor disk for the rotor of a non-positive displacement machine with at least one borehole extending in an axial direction. The aim of the invention is to provide a rotor disk for a non-positive displacement machine that has an increased serviceable life. To this end, the boring extends in an at least partially convex manner whereby having an enlarged diameter in the middle area in order to increase internal compressive stress an to reduce tangential stresses.

Abstract translation: 本发明涉及一种用于非正排量机的转子的转子盘，其具有沿轴向延伸的至少一个钻孔。 本发明的目的是提供一种具有增加的使用寿命的用于非正排量机器的转子盘。 为此，钻孔以至少部分凸起的方式延伸，由此在中间区域具有增大的直径以便增加内部压缩应力以减少切向应力。

公开(公告)号：US06602049B2

公开(公告)日：2003-08-05

申请号：US09953143

申请日：2001-09-17

Applicant: Jean-Pierre Caubet ,  Daniel Dao ,  Antoine Jean ,  Didier Merville

Inventor： Jean-Pierre Caubet ,  Daniel Dao ,  Antoine Jean ,  Didier Merville

IPC: F04D2944

CPC classification number: F04D29/563 ,  F01D5/143 ,  F01D17/162 ,  F05D2250/19 ,  F05D2250/29 ,  Y02T50/673

Abstract: In a turbomachine compressor stator comprising a plurality of variable-pitch vanes (36), each vane mounted in rotation, about an axis of pivoting (38), in a wall (34) forming a surface of revolution about a longitudinal central axis of rotation of the turbomachine (32), being inclined by a specified angle (&agr;) with respect to a plane perpendicular to this longitudinal central axis, there is provision for this wall to be machined locally opposite an end part of each vane (42) so as to form a spherical portion or pocket (40) whose center is positioned on the axis of pivoting and whose radius is determined so as to ensure, over the entire range of operation of the vane, a predetermined minimum clearance between this end part of each vane and the opposite machined spherical pocket while limiting the depth of machining of this pocket.

公开(公告)号：US08328513B2

公开(公告)日：2012-12-11

申请号：US12650876

申请日：2009-12-31

Applicant: Kevin R. Kirtley

Inventor： Kevin R. Kirtley

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/143 ,  F01D5/145 ,  F04D29/541 ,  F05D2240/121 ,  F05D2250/182 ,  F05D2250/19 ,  F05D2250/193 ,  F05D2270/17

Abstract: A row of stator blades in a compressor of a combustion turbine engine, the combustion turbine engine including a diffuser located downstream of the compressor, and the row of stator blades disposed in close proximity to the diffuser; the row of stator blades comprising: a plurality of stator blades that include at least one of an inboard forward notch and an outboard forward notch.

Abstract translation: 在燃气涡轮发动机的压缩机中的一排定子叶片，所述燃气涡轮发动机包括位于压缩机下游的扩散器，以及靠近扩散器设置的一排定子叶片; 所述一排定子叶片包括：多个定子叶片，其包括内侧前槽和外侧前槽中的至少一个。

公开(公告)号：US07195454B2

公开(公告)日：2007-03-27

申请号：US11002570

申请日：2004-12-02

Applicant: Wenfeng Lu ,  Ching-Pang Lee ,  Nicholas Charles Palmer

Inventor： Wenfeng Lu ,  Ching-Pang Lee ,  Nicholas Charles Palmer

IPC: F03B1/04 ,  F03B3/16

CPC classification number: F01D5/143 ,  F01D5/145 ,  F01D9/041 ,  F01D11/005 ,  F01D25/246 ,  F05D2250/19 ,  Y02T50/673

Abstract: A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and suction sides. The flowpath surface joins the first endface at the forward edge in a forward bullnose and joins the second endface at the aft edge in an aft bullnose, with the bullnoses varying in radius from the opposite edges.

Abstract translation: 涡轮机翼型包括从流路表面跨越的相对的压力和吸力侧。 流路表面具有弦向相反的前后边缘，并且与翼型压力和吸力侧对应的横向相对的第一和第二端面。 流路表面将前端长嘴的前边缘处的第一端面连接起来，并且在后方长臂处的后边缘处连接第二端面，其中棱镜从相对边缘的半径变化。

公开(公告)号：US06910860B2

公开(公告)日：2005-06-28

申请号：US10452428

申请日：2003-05-30

Applicant: Samuel L. Glover ,  Thomas E. Manning

Inventor： Samuel L. Glover ,  Thomas E. Manning

IPC: F02K3/06 ,  F01D9/04 ,  F04D29/52 ,  F04D29/54 ,  F04D29/64 ,  F01D1/02

CPC classification number: F04D29/644 ,  F01D9/042 ,  F04D29/542 ,  F05D2220/36 ,  F05D2230/10 ,  F05D2250/19 ,  F05D2250/29 ,  Y02T50/671 ,  Y10T29/49323

Abstract: The present invention relates to an improved system for installing a vane in a gas turbine. The system includes a receptor pocket positioned within a first support structure and a boot attached to a first or inner end of a vane for insertion into the receptor pocket. In a first embodiment of the present invention, the receptor pocket is formed by machining it into the support structure. In a second embodiment of the present invention, the receptor pocket is formed by an insert which is installed into the support structure. In accordance with the present invention, the inner end of the vane having the boot is first inserted into the receptor pocket. After insertion has been completed, the vane is rotated until an outer base is brought into position against an outer support structure. The outer end of the vane is then secured to the outer support structure using studs and nuts.

Abstract translation: 本发明涉及一种用于在燃气轮机中安装叶片的改进系统。 该系统包括定位在第一支撑结构内的接收器袋和附接到叶片的第一或内端的靴子以用于插入到接收器袋中。 在本发明的第一实施例中，通过将其加工成支撑结构形成接收器袋。 在本发明的第二实施例中，接收器槽由安装到支撑结构中的插入件形成。 根据本发明，具有护罩的叶片的内端首先插入到接收器袋中。 插入完成后，叶片旋转直到外部基座相对于外部支撑结构进入位置。 然后使用螺栓和螺母将叶片的外端固定到外支撑结构。

公开(公告)号：US06789316B2

公开(公告)日：2004-09-14

申请号：US10604321

申请日：2003-07-10

Applicant: Jan Häggander ,  Jan Lundgren

Inventor： Jan Häggander ,  Jan Lundgren

IPC: B23P1500

CPC classification number: F02K9/64 ,  F02K9/97 ,  F05D2230/20 ,  F05D2250/19 ,  F05D2250/292 ,  F05D2250/71 ,  F05D2260/20 ,  Y10T29/49346 ,  Y10T29/49826 ,  Y10T29/49995

Abstract: Method and arrangement for manufacturing an outlet nozzle (10) for use in a liquid fuel rocket engine. The nozzle forms a body of revolution having an axis of revolution and a cross section that varies in diameter along said axis. The nozzle has a wall structure comprising a plurality of mutually adjacent cooling channels extending substantially in parallel from the inlet end (12) of the nozzle to its outlet end (13). The method includes providing a plurality of preprocessed profile members, each having a web and flanges in opposite directions from said web. Each profile member is machined to present a longitudinally gradually tapering width. The member is curved to conform with the wall section of the nozzle, and members are joined by welding the flanges to form a bell-shaped nozzle structure with cooling channels (11) formed by adjacent webs and adjacent pairs of flanges.

Abstract translation: 用于制造用于液体燃料火箭发动机的出口喷嘴（10）的方法和装置。 喷嘴形成具有沿所述轴线的直径变化的旋转轴线和截面的旋转体。 喷嘴具有包括多个相互相邻的冷却通道的壁结构，冷却通道从喷嘴的入口端（12）基本上平行延伸到其出口端（13）。 该方法包括提供多个预处理轮廓构件，每个预成型轮廓构件具有腹板和与所述腹板相反方向的凸缘。 每个轮廓构件被加工以呈现纵向逐渐变窄的宽度。 该构件被弯曲以符合喷嘴的壁部分，并且通过焊接凸缘来连接构件以形成钟形喷嘴结构，其具有由相邻的腹板和相邻的凸缘对形成的冷却通道（11）。

公开(公告)号：US07955047B2

公开(公告)日：2011-06-07

申请号：US11895429

申请日：2007-08-24

Applicant: Juerg Spuler

Inventor： Juerg Spuler

IPC: F01D17/14

CPC classification number: F01D17/143 ,  F02C6/12 ,  F05D2220/40 ,  F05D2250/14 ,  F05D2250/16 ,  F05D2250/19 ,  F05D2250/192 ,  F05D2250/193 ,  F05D2250/62 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/96

Abstract: Variable geometry turbine, in particular a gas turbine, comprising a housing (2, 22), a turbine rotor (4), a fluid inlet scroll (1) that surrounds the turbine rotor, a vaned nozzle interposed between the inlet scroll and the turbine rotor conceived to accelerate the flow of fluid, the nozzle comprising an axially adjustable ring (5, 25) conceived to vary the nozzle gap (3, 23) and having a wall (19) delimiting the nozzle gap, the wall having balance holes (6, 26, 26′) connecting the nozzle gap with a chamber (12) delimited by the housing and the ring, characterised in that the edges (16), formed by the holes with the surface (18) of the wall facing the nozzle gap, are rounded in the portion (17, 17′) located downstream the holes with respect to the fluid flow. Turbocharger and supercharged engine comprising the engine.

Abstract translation: 可变几何涡轮机，特别是燃气涡轮机，包括壳体（2,22），涡轮机转子（4），围绕涡轮机转子的流体入口涡旋件（1），插入在入口涡旋件和涡轮机 被设想为加速流体流动的喷嘴，喷嘴包括轴向可调节的环（5,52），其被设想为改变喷嘴间隙（3,23）并且具有限定喷嘴间隙的壁（19），壁具有平衡孔 将所述喷嘴间隙与由所述壳体和所述环限定的腔室（12）连接，其特征在于，由所述孔形成的所述边缘（16）与所述壁的面向所述喷嘴的所述表面（18） 间隙在相对于流体流动位于孔下游的部分（17,17'）中圆化。 包括发动机的涡轮增压器和增压发动机。

公开(公告)号：US20080145208A1

公开(公告)日：2008-06-19

申请号：US11642002

申请日：2006-12-19

Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Scott David Hunter

Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Scott David Hunter

IPC: F04D29/08 ,  F01D9/02

CPC classification number: F01D5/145 ,  F01D5/082 ,  F01D5/143 ,  F01D9/041 ,  F01D11/001 ,  F05D2250/19 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine stage includes a stator nozzle cooperating with a row of turbine blades. The nozzle includes a row of vanes mounted between inner and outer bands, with the inner band adjoining the blades at inner platforms thereof at a rotary seal. The inner band includes a stator bullnose at the trailing edge thereof cooperating with the rotary seal for reducing aerodynamic losses thereat.

Abstract translation: 涡轮级包括与一排涡轮叶片配合的定子喷嘴。 喷嘴包括安装在内带和外带之间的一排叶片，内带在其内平台处以旋转密封件邻接叶片。 内带在其后缘包括一个与旋转密封件配合的定子公牛，以减少其中的空气动力学损失。

公开(公告)号：US06542843B1

公开(公告)日：2003-04-01

申请号：US09562239

申请日：2000-04-28

Applicant: Peter Metzinger ,  Rupert Stelzer ,  Reimund Haimerl ,  Georg Muschal ,  Arndt Glaesser

Inventor： Peter Metzinger ,  Rupert Stelzer ,  Reimund Haimerl ,  Georg Muschal ,  Arndt Glaesser

IPC: G06F1900

CPC classification number: B23P6/002 ,  B23P13/02 ,  B23P15/006 ,  F01D5/005 ,  F05D2250/19 ,  F05D2250/29

Abstract: A method for producing matched surfaces on rotor units with integral blades comprising a hub and at least one blade ring, by removing by machine after integral joining with component overmeasure in the area of the joining zone, whereby at least one actual surface is acquired by measuring method, and a surface matching it, is produced. Acquisition by measuring method and production take place on a process machine in one clamping of the rotor unit. The desired surface of each processing area is provided in the form of stored data. Starting from at least one measured actual surface, a matched surface is produced beyond the joining zone, with the surface everywhere adjoining the actual surface and/or a so-called repair surface of which there is at least one, without any kinks or steps at a specifiable minimum curvature. As far as is possible, the surface itself corresponds to a mathematically continuous spatial surface comprising a locally and/or direction-dependent variably-specifiable minimum curvature, whereby approximation to the desired profile takes precedence over approximation to the desired position.

Abstract translation: 一种用于在具有集成叶片的转子单元上制造匹配表面的方法，所述转子单元包括轮毂和至少一个叶片环，通过在接合区域的区域中与部件过量度整体接合之后通过机器移除，由此通过测量获得至少一个实际表面 方法和与其匹配的表面。 通过测量方法和生产在一个夹紧转子单元的过程中进行采集。 每个处理区域的所需表面以存储数据的形式提供。 从至少一个测量的实际表面开始，在连接区域之外产生匹配的表面，其中表面处于与实际表面相邻的地方和/或所谓的修复表面，其中至少有一个，没有任何扭结或阶梯 一个可指定的最小曲率。 尽可能地，表面本身对应于包括局部和/或方向依赖的可变特定最小曲率的数学上连续的空间表面，由此近似于所需轮廓优先于近似于期望位置。