公开(公告)号：US08555655B2

公开(公告)日：2013-10-15

申请号：US12140094

申请日：2008-06-16

申请人： Urs Benz ,  Jonas Hurter ,  Thorsten Motzkus

发明人： Urs Benz ,  Jonas Hurter ,  Thorsten Motzkus

IPC分类号： F02C7/28 ,  F02C7/30

CPC分类号： F01D11/005 ,  F01D9/023

摘要： A turbomachine with at least one combustion chamber and at least one turbine which lies downstream of it. The turbine has at least one support element and a lining element connected to the support element and formed as a heat shield. A gap sealed by means of a seal, is formed between the at least one combustion chamber and the turbine, an exchangeable insert is arranged in the gap on the end face on the support element and protects at least the support element against hot gases which penetrate into the gap, and against oxidation which is associated with it.

摘要翻译： 具有至少一个燃烧室的涡轮机和位于其下游的至少一个涡轮机。 涡轮机具有至少一个支撑元件和连接到支撑元件并形成为隔热罩的衬里元件。 在所述至少一个燃烧室和所述涡轮机之间形成有通过密封件密封的间隙，在所述支撑元件的端面上的所述间隙中布置有可交换的插入件，并且至少保护所述支撑元件免受穿透的热气体 进入间隙，并防止与之相关的氧化。

公开(公告)号：US20080230997A1

公开(公告)日：2008-09-25

申请号：US11592277

申请日：2006-11-03

申请人： Ian William Boston ,  Stefan Gross ,  Jonas Hurter ,  Thomas Kueenzi

发明人： Ian William Boston ,  Stefan Gross ,  Jonas Hurter ,  Thomas Kueenzi

IPC分类号： F01D11/02

CPC分类号： F23R3/002 ,  F23R2900/00012

摘要： A combustion chamber for an industrial gas turbine has thermal protective elements which are installed along the inner circumference of its casing. The thermal protective elements are cooled by cooling air which is added to the fuel in the region in front of a front casing section after the cooling. A brush seal is installed between the front casing section and the thermal protective elements, where the brush seal is configured in segments. The combustion chamber can be sealed against leakages of cooling air in all operating states of the combustion chamber.

摘要翻译： 用于工业燃气轮机的燃烧室具有沿其壳体的内周安装的热保护元件。 热保护元件由冷却后的冷却空气冷却，该冷却空气在冷却后的前壳体部分的前方的区域内被添加到燃料中。 刷子密封件安装在前壳体部分和热保护元件之间，其中刷密封件被构造成段。 燃烧室可以在燃烧室的所有操作状态下被密封以防止冷却空气的泄漏。

公开(公告)号：US07065971B2

公开(公告)日：2006-06-27

申请号：US10792709

申请日：2004-03-05

申请人： Valter Bellucci ,  Jonas Hurter ,  Joerg Pross

发明人： Valter Bellucci ,  Jonas Hurter ,  Joerg Pross

IPC分类号： F23R3/02

CPC分类号： F02B77/13 ,  F05B2260/96 ,  F23R3/04 ,  F23R2900/00014 ,  Y02T50/675

摘要： Combustion driven pressure pulsations may limit the range of operating conditions where a modern gas turbine can operate with low emission and high efficiency performance. The control of acoustic vibrations has been consequently growing as an essential issue in gas turbine design, development and maintenance. The basic idea of the present invention is to use cooling air leakage through the gaps (7) of combustor liner segments (3;4) to get acoustic damping of combustion pulsations. The main component of the design is the sealing device (8) which covers the gap (7) between the two liner segments (3) and (4). The sealing device (8) collects in the plenum (9) some of the cooling air (6) flowing between the outer casing (1) and the inner liner structure (2). For this purpose the sealing device (8) is provided with openings (12) along the side walls (10) which allow the cooling air (6) to enter the plenum (9). In the plenum (9) the cooling air (6) is distributed along the gap (7) and discharged through openings (13), distributed along the top side (11) of the sealing device (8). The jets (18) discharged through the openings (13) achieve the additional effect to dampen acoustic pulsations in the combustion chamber (17).

摘要翻译： 燃烧驱动的压力脉动可能限制现代燃气轮机可以以低排放和高效率运行的操作条件的范围。 因此，声波振动的控制作为燃气轮机设计，开发和维护中的一个重要问题而日益增长。 本发明的基本思想是使用通过燃烧器衬套段（3; 4）的间隙（7）的冷却空气泄漏来获得燃烧脉动的声阻尼。 设计的主要部件是覆盖两个衬垫段（3）和（4）之间的间隙（7）的密封装置（8）。 密封装置（8）在集气室（9）中收集在外壳（1）和内衬层结构（2）之间流动的一些冷却空气（6）。 为此，密封装置（8）沿着侧壁（10）设有允许冷却空气（6）进入增压室（9）的开口（12）。 在集气室（9）中，冷却空气（6）沿着间隙（7）分布并通过沿着密封装置（8）的顶侧（11）分布的开口（13）排出。 通过开口（13）排出的喷嘴（18）实现了抑制燃烧室（17）中的声波脉动的附加效果。

公开(公告)号：US08052155B2

公开(公告)日：2011-11-08

申请号：US11278438

申请日：2006-04-03

申请人： Peter Graham Amos ,  Ian William Boston ,  Kennet W. Cornett ,  Jonas Hurter ,  Dominick Gregory More ,  Markus Stemann ,  Alexander Zagorskiy

发明人： Peter Graham Amos ,  Ian William Boston ,  Kennet W. Cornett ,  Jonas Hurter ,  Dominick Gregory More ,  Markus Stemann ,  Alexander Zagorskiy

IPC分类号： F16J15/02 ,  F16J15/08

CPC分类号： F16J15/0887 ,  F23M2900/05005 ,  F23R3/002 ,  F23R2900/00012

摘要： A seal (1) includes a first component (7) and second component (9), the first component including a first material having a high thermal and oxidation and wear resistance, and the second component (9) including a second material that is different from the first material and has a high spring load maintenance. The seal (1) is applied to a combustion chamber for a gas turbine, where the first component (7) extends between the casing wall of the combustion chamber and adjacent liner segments (4). The spring load of the second component (9) provides a seal also in the case of vibrations in a combustion chamber. The lifetime of the seal (1) is increased due to the individual materials, which are optimally chosen for the functions of high thermal and wear resistance and spring load maintenance respectively. The seal is further applied to the sealing between adjacent stationary blade platforms in gas turbines.

摘要翻译： 密封件（1）包括第一部件（7）和第二部件（9），第一部件包括具有高热和氧化和耐磨性的第一材料，第二部件（9）包括不同的第二部件 从第一种材料并具有较高的弹簧载荷维护。 密封件（1）被施加到用于燃气轮机的燃烧室，其中第一部件（7）在燃烧室的壳体壁和相邻的衬套段（4）之间延伸。 第二部件（9）的弹簧载荷在燃烧室中的振动的情况下也提供密封。 密封件（1）的寿命由于单独的材料而增加，这些材料分别适用于高耐热和耐磨性和弹簧载荷维护的功能。 密封件进一步应用于燃气轮机中相邻固定叶片平台之间的密封。

公开(公告)号：US20060062664A1

公开(公告)日：2006-03-23

申请号：US11249625

申请日：2005-10-14

申请人： Nicolas Campino Johnson ,  Matthias Hoebel ,  Jonas Hurter ,  Christoph Niederberger

发明人： Nicolas Campino Johnson ,  Matthias Hoebel ,  Jonas Hurter ,  Christoph Niederberger

IPC分类号： F01D5/20

CPC分类号： F01D11/12 ,  F01D11/08 ,  F01D21/04

摘要： The invention discloses a thermal turbomachine having at least one row of rotor blades (1). At least one first rotor blade (1) has a greater radial length than the others and at the blade tip (2) is equipped with a first abrasive layer (72). At least one rotor blade (1) which has a shorter radial length than the first rotor blade (1) is equipped with a second abrasive layer (71) at the blade tip (2). The first abrasive layer (72) has a better cutting capacity and a lower thermal stability than the second abrasive layer (71). During commissioning of the thermal turbomachine, the first abrasive layer (72) is in contact with the abradable layer of the stator (8), and during continuous operation of the thermal turbomachine the second abrasive layer (71) is in contact with the abradable layer of the stator (8).

摘要翻译： 本发明公开了一种具有至少一排转子叶片（1）的热涡轮机。 至少一个第一转子叶片（1）具有比其它第一转子叶片（1）更大的径向长度，并且在叶片尖端（2）上配备有第一研磨层（7,2N）。 具有比第一转子叶片（1）更短的径向长度的至少一个转子叶片（1）在叶片尖端（2）处装备有第二研磨层（7I 1）。 第一研磨层（7,2N）具有比第二研磨层（7 SUB）更好的切割能力和更低的热稳定性。 在热式涡轮机的调试期间，第一研磨层（7,2N）与定子（8）的可磨损层接触，并且在热涡轮机的连续操作期间，第二研磨层（7 1＆lt; 1＆gt;）与定子（8）的可磨损层接触。

公开(公告)号：US20050150232A1

公开(公告)日：2005-07-14

申请号：US10830103

申请日：2004-04-23

申请人： Rolf Dittmann ,  Jonas Hurter ,  Robert Marmilic ,  Pierre Meylan ,  Ernst Pauli

发明人： Rolf Dittmann ,  Jonas Hurter ,  Robert Marmilic ,  Pierre Meylan ,  Ernst Pauli

IPC分类号： F01D25/12 ,  F01D25/26 ,  F02C7/12 ,  F02C7/18

CPC分类号： F02C7/12 ,  F01D25/12 ,  F01D25/26 ,  F05D2260/20

摘要： In order to avoid the “buckling” of multi-shell turbomachine casings during a cooling phase following the shutdown, it is proposed to provide means in order to suitably discharge warm medium which collects at a point of the casing cavity situated at the highest geodetic level. In an embodiment, it is proposed to allow the corresponding lines to open out in the stack of a power plant; the stack draft effect assists the flow even further. Regulating members are advantageously provided in the lines in order to shut off these lines during operation of the turbomachine on the one hand and in order not to arrange the flow through the casing cavities too intensively on the other hand.

摘要翻译： 为了避免关闭后的冷却阶段的多壳涡轮机壳体的“弯曲”，提出了为了适当地排出收集在位于最高大地测量位置的壳体腔的点处的温暖介质的装置 。 在一个实施例中，提出允许相应的线在发电厂的堆叠中打开; 堆垛效果有助于进一步的流动。 有利地，调节构件设置在管线中，以便一方面在涡轮机操作期间切断这些管线，并且另一方面为了不使流过套管腔的流动过度集中。

公开(公告)号：US08783044B2

公开(公告)日：2014-07-22

申请号：US12824630

申请日：2010-06-28

申请人： Ulrich Steiger ,  Jonas Hurter

发明人： Ulrich Steiger ,  Jonas Hurter

IPC分类号： F02C7/12 ,  F01D5/14 ,  F01D5/18 ,  F01D9/02

CPC分类号： F01D5/186 ,  F01D9/023 ,  F05B2240/801 ,  F05D2240/81

摘要： In a gas turbine, a plurality of burners, which are arranged concentrically to the rotational axis in a regular arrangement, each directing hot gas through an associated combustion chamber outlet into a turbine, at the inlet of which a second plurality of stator blades are arranged in a ring, uniformly spaced apart around the rotational axis. Cooling openings are provided, which are distributed over the circumference, through which cooling air is injected into the hot gas flow at the combustion chamber outlet. An improvement of the flow conditions in the hot gas is achieved by the cooling openings being divided into first cooling opening groups and second cooling opening groups. The arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades, and in that the arrangement of the second cooling opening groups corresponds to the regular arrangement of the burners.

摘要翻译： 在燃气轮机中，多个燃烧器以规则的排列与旋转轴线同心地布置，每个燃烧器将热气体通过相关联的燃烧室出口引导到涡轮机中，在其入口处布置有第二多个定子叶片 环绕旋转轴线均匀间隔开。 设置有冷却开口，其分布在圆周上，冷却空气通过该开口喷射到燃烧室出口处的热气流中。 通过将冷却开口分成第一冷却开口组和第二冷却开口组来实现热气体中流动条件的改善。 第一冷却开口组的布置对应于定子叶片的布置，并且第二冷却开口组的布置对应于燃烧器的规则排列。

公开(公告)号：US07631501B2

公开(公告)日：2009-12-15

申请号：US11067722

申请日：2005-03-01

申请人： Ian William Boston ,  Kenneth W. Cornett ,  Hans-Martin Hocke ,  Jonas Hurter ,  Dominick Greg More

发明人： Ian William Boston ,  Kenneth W. Cornett ,  Hans-Martin Hocke ,  Jonas Hurter ,  Dominick Greg More

IPC分类号： F02C1/00 ,  F02G3/00

CPC分类号： F23R3/28 ,  F02C7/28 ,  F16J15/0887 ,  F23R3/60

摘要： The present invention relates to a sealing body for sealing an outer component with respect to an inner component, in particular for a combustion chamber of a gas turbine. The outer component has a passage opening, through which the inner component projects out of the outer component. In the installed state, the sealing body is arranged in the region of the passage opening, surrounds the inner component in a circumferentially continuous manner, bears in a circumferentially continuous manner, by means of an inner sealing zone, against an outer sealing surface of the inner component and bears in a circumferentially continuous manner, by means of an outer sealing zone, against an inner sealing surface of the outer component. The sealing body is produced by deformation from at least one metal sheet that is in strip form and is circumferentially continuous. The inner sealing zone and the outer sealing zone are formed at a profiled section of the sealing body along the entire circumference.

摘要翻译： 本发明涉及一种用于密封外部部件相对于内部部件，特别是用于燃气轮机的燃烧室的密封体。 外部部件具有通道开口，内部部件通过该通道开口伸出外部部件。 在安装状态下，密封体布置在通道开口的区域中，以周向连续的方式围绕内部部件，通过内部密封区域周向连续地抵靠外部密封表面 内部部件，并且通过外部密封区域以周向连续的方式承载在外部部件的内部密封表面上。 密封体通过从至少一种带状形式的金属板的变形产生，并且是周向连续的。 内密封区域和外密封区域沿着整个圆周形成在密封体的成型部分。

公开(公告)号：US20080213096A1

公开(公告)日：2008-09-04

申请号：US11838530

申请日：2007-08-14

申请人： Nicolas Johnson Campino ,  Jonas Hurter ,  Markus Stemann ,  Sergey Trifonov ,  Alexander Zagorskiy

发明人： Nicolas Johnson Campino ,  Jonas Hurter ,  Markus Stemann ,  Sergey Trifonov ,  Alexander Zagorskiy

IPC分类号： F01D11/08

CPC分类号： F16J15/027 ,  F01D11/005 ,  F05D2260/20 ,  F16J15/0893 ,  Y10S277/93

摘要： A sealing element for sealing a component gap with respect to a flow, in particular for use in a fluid-flow machine, specifically in a turbomachine is provided. In addition a fluid-flow machine is provided including such a sealing element for sealing a component gap. The sealing element includes a hollow profile enclosing a cavity. Arranged in the hollow profile are a first opening and a second opening, which are spaced apart from each other in the longitudinal direction of the hollow profile. The first opening is formed as an inlet opening for a cooling fluid into the cavity of the hollow profile, the second opening is formed as an outlet opening for the cooling fluid from the cavity of the hollow profile. With the sealing element arranged in a fluid-flow machine, the sealing element can consequently be internally cooled by means of the cooling fluid. Furthermore, the sealing element uses the pressure gradient occurring in the flow in the direction of flow to form a stable cooling fluid flow.

摘要翻译： 提供了用于相对于流动密封部件间隙的密封元件，特别是用于流体流动机械，特别是在涡轮机中的密封元件。 此外，提供了流体流动机器，其包括用于密封部件间隙的这种密封元件。 密封元件包括封闭空腔的中空型材。 排列在中空型材中的第一开口和第二开口在中空型材的纵向彼此间隔开。 第一开口形成为用于冷却流体进入中空型材的空腔的入口，第二开口形成为来自中空型材的空腔的冷却流体的出口。 由于密封元件布置在流体流动机器中，密封元件因此可以通过冷却流体内部冷却。 此外，密封元件使用在流动方向上的流动中产生的压力梯度以形成稳定的冷却流体流动。

公开(公告)号：US07329084B2

公开(公告)日：2008-02-12

申请号：US10830028

申请日：2004-04-23

申请人： Rolf Dittmann ,  Jonas Hurter ,  Robert Marmilic ,  Pierre Meylan ,  Ernst Pauli

发明人： Rolf Dittmann ,  Jonas Hurter ,  Robert Marmilic ,  Pierre Meylan ,  Ernst Pauli

IPC分类号： F01D25/26 ,  F01D25/12

CPC分类号： F01D25/12 ,  F01D25/26 ,  F05D2260/601 ,  Y02T50/675

摘要： Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow which in turn excites the flow, preferably a circumferential flow or a helical flow. The invention is suitable in particular for avoiding casing distortions when turbomachines are at rest.

摘要翻译： 用于驱动流动的合适装置布置在特别在涡轮机的多壳壳体中形成的环形或环形节段空腔中。 在空腔内布置的是通过合适的装置供应的喷射器，其具有运动流体流，其又激发流动，优选地周向流动或螺旋流动。 本发明特别适用于在涡轮机静止时避免壳体扭曲。