公开(公告)号：US20090208344A1

公开(公告)日：2009-08-20

申请号：US11667332

申请日：2005-09-16

申请人： Rene Jabado ,  Uwe Kaden ,  Ursus Krüger ,  Daniel Körtvelyessy ,  Ralph Reiche ,  Michael Rindler ,  Jan Steinbach ,  Peter Tiemann ,  Iris Oltmanns

发明人： Rene Jabado ,  Uwe Kaden ,  Ursus Krüger ,  Daniel Körtvelyessy ,  Ralph Reiche ,  Michael Rindler ,  Jan Steinbach ,  Peter Tiemann ,  Iris Oltmanns

IPC分类号： F01D5/18 ,  C25D5/02 ,  C25D21/12

CPC分类号： B23H9/14 ,  B23H9/00 ,  B23H9/10 ,  B23H9/16 ,  C25D5/026 ,  C25D7/04 ,  C25F3/14

摘要： There is described a method wherein through holes of a wall are treated on a inside, and wherein one respective pole electrode is assigned to each through hole that is to be processed.

摘要翻译： 描述了一种方法，其中在内部处理壁的通孔，并且其中一个相应的极电极被分配给要被处理的每个通孔。

公开(公告)号：US20100257869A1

公开(公告)日：2010-10-14

申请号：US10568736

申请日：2004-07-16

申请人： Christian Cornelius ,  Reinhard Mönig ,  Peter Tiemann ,  Iris Oltmanns

发明人： Christian Cornelius ,  Reinhard Mönig ,  Peter Tiemann ,  Iris Oltmanns

IPC分类号： F02C6/08 ,  F02C7/04 ,  F02C7/18 ,  F02C7/20

CPC分类号： F01D25/12 ,  F23R3/005

摘要： The invention relates to a gas turbine, comprising an annular combustion chamber and an upstream diffuser, with a throughflow essentially parallel to a turbine longitudinal axis, at a distance from said axis at least partly less than the annular combustion chamber, in which a compressed gas may be divided into several partial flows at a branching point, whereby at least one of the partial flows is a cooling gas flow. A main deflection region is provided in said diffuser, directed at an angle to the turbine longitudinal axis towards the annular combustion chamber.

摘要翻译： 本发明涉及一种燃气轮机，其包括环形燃烧室和上游扩散器，其具有基本上平行于涡轮纵向轴线的通流，所述通流至少部分地小于环形燃烧室，所述通气流至少部分地小于环形燃烧室，其中压缩气体 可以在分支点处分成几个部分流，由此部分流中的至少一个是冷却气体流。 主偏转区域设置在所述扩散器中，朝向环形燃烧室与涡轮纵向轴线成一定角度。

公开(公告)号：US20090003996A1

公开(公告)日：2009-01-01

申请号：US12202535

申请日：2008-09-02

申请人： Peter Tiemann ,  Iris Oltmanns

发明人： Peter Tiemann ,  Iris Oltmanns

IPC分类号： F02C7/28

CPC分类号： F01D5/3015 ,  F01D11/001 ,  F01D11/006 ,  F01D11/02 ,  F16J15/4476 ,  Y10T29/49323

摘要： The invention relates to a segmented inner ring for holding guide blades. According to the invention, a lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially, and respectively one half of a labyrinth seal is formed on the front side of the inner ring and on the shaft shoulder. The aim of the invention is to apply an arrangement of stacked labyrinth seals, known from aeroplane turbines, to a stationary gas turbine having a separation plane. To this end, a method is used to mount an inner ring of a gas turbine. The invention also relates to a stationary gas turbine comprising a segmented inner ring.

摘要翻译： 本发明涉及一种用于保持导向叶片的分段内圈。 根据本发明，形成在转子轴上的与内圈的前侧相对的侧壁和径向延伸的轴肩分别形成在内圈的前侧上的迷宫式密封件的一半， 轴肩。 本发明的目的是应用从飞机涡轮机已知的堆叠的迷宫式密封件到具有分离平面的固定式燃气轮机的布置。 为此，使用一种方法来安装燃气轮机的内环。 本发明还涉及一种包括分段内环的固定式燃气轮机。

公开(公告)号：US20060037321A1

公开(公告)日：2006-02-23

申请号：US10524523

申请日：2003-08-01

申请人： Peter Tiemann ,  Iris Oltmanns

发明人： Peter Tiemann ,  Iris Oltmanns

IPC分类号： F23R3/42

CPC分类号： F23M7/04 ,  F23R3/005

摘要： A gas turbine combustion chamber comprises a manhole as access to a combustion chamber interior, which may be sealed with a manhole cover. The manhole comprises an inner cooling chamber and may thus take particularly high thermal loads.

摘要翻译： 燃气轮机燃烧室包括作为进入燃烧室内部的人孔，其可以用人孔盖密封。 井孔包括内部冷却室，并且因此可以采取特别高的热负荷。

公开(公告)号：US20050120942A1

公开(公告)日：2005-06-09

申请号：US10486606

申请日：2002-07-24

申请人： Peter Tiemann ,  Iris Oltmanns

发明人： Peter Tiemann ,  Iris Oltmanns

IPC分类号： B22D27/04 ,  C30B11/00 ,  C30B29/52 ,  C30B1/00

CPC分类号： C30B11/003 ,  C30B11/00 ,  C30B29/52

摘要： The invention relates to a method for producing a monocrystalline component, having a complex moulded structure with different structure parts, from a molten metal. According to the method, said molten metal is located in a negative mould, corresponding to the moulding structure and said negative mould moves with the formation of a solidification front on a temperature drop, which is adapted to the crystallization speed of the molten metal and which includes the melting point. Said method is characterized in that at least one of the structure parts of the moulded structure experiences an individual temperature drop. If the solidification front has to grow through a structure part, which is inappropriately oriented in relation to the solidification front, said structure part or zone can experience an individual temperature drop. This enables monocrystalline components, having a complex moulded structure, to be produced in a reliable and economic manner.

摘要翻译： 本发明涉及一种从熔融金属制备具有不同结构部分的复合成型结构的单晶组分的方法。 根据该方法，所述熔融金属位于负模具中，对应于模制结构，并且所述负模具在形成凝固正面的温度下移动，温度下降，其适合熔融金属的结晶速度，并且其中 包括熔点。 所述方法的特征在于，模制结构的至少一个结构部件经历单独的温度降。 如果固化前沿必须通过相对于固化前沿不适当取向的结构部分生长，则所述结构部分或区域可以经历单独的温度下降。 这使得具有复杂模制结构的单晶组分可以以可靠和经济的方式生产。

公开(公告)号：US20090272120A1

公开(公告)日：2009-11-05

申请号：US12500816

申请日：2009-07-10

申请人： Peter Tiemann ,  Iris Oltmanns

发明人： Peter Tiemann ,  Iris Oltmanns

IPC分类号： F02C6/08 ,  F02C1/00

CPC分类号： F23R3/04 ,  F01D25/12 ,  F23R3/26 ,  Y02T50/675

摘要： The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber, with generation of a hot working medium, with an annular diffuser arranged coaxially to the rotor, between the compressor and the annular combustion chamber, for distribution and deflection of the fluid, whereby a part of the fluid is diverted as cooling fluid for the turbine stages after the combustion chamber, by means of a dividing element, arranged in the fluid flow. According to the invention, a compact diffuser and an economical gas turbine with an improved flow for the diversion of cooling air may be achieved, whereby the annular dividing element, arranged coaxially to the rotor, comprises at least one opening, facing the fluid flow and the dividing element is supported on the diffuser, by means of several hollow rib-like support elements, by means of which the cooling fluid, diverted through the opening, is first directed towards the rotor.

公开(公告)号：US20050076503A1

公开(公告)日：2005-04-14

申请号：US10486607

申请日：2002-07-24

申请人： Ursula Pickert ,  Peter Tiemann ,  Iris Oltmanns

发明人： Ursula Pickert ,  Peter Tiemann ,  Iris Oltmanns

IPC分类号： B23K20/02 ,  B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F02C7/00 ,  B63H1/26 ,  F03B3/12

CPC分类号： B23P15/04 ,  F01D5/147 ,  F01D5/181 ,  F05D2220/3215 ,  F05D2300/133 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49893

摘要： The invention relates to a blade for a turbine engine with a base body, made from a titanium alloy, with a first and a second component piece, which are connected in the connection region by means of a bonding process. A groove with a groove wall runs through the connection region, to prevent local concentration of tension, such that the above borders directly on the second component piece and forms therewith a connection angle greater than 70 degrees.

摘要翻译： 本发明涉及一种具有基体的涡轮发动机叶片，该基体由钛合金制成，具有第一和第二部件，它们通过接合工艺连接在连接区域中。 具有凹槽壁的凹槽穿过连接区域，以防止局部的张力集中，使得上述边界直接在第二组件上，并形成大于70度的连接角度。

公开(公告)号：US20070062198A1

公开(公告)日：2007-03-22

申请号：US10558893

申请日：2004-04-27

申请人： Michael Huth ,  Peter Tiemann ,  Iris Oltmanns

发明人： Michael Huth ,  Peter Tiemann ,  Iris Oltmanns

IPC分类号： F23R3/02

CPC分类号： F23R3/005

摘要： The invention relates to a combustion chamber of a gas turbine, inside of which a supplied fuel is reacted with supplied combustion air in order to produce a working medium. The inside of the combustion chamber wall is provided with a lining formed from a number of heat shield elements. The or each heat shield element, together with the combustion chamber wall, forms an interior space that can be subjected to the action of a coolant. The aim of the invention is to provide a combustion chamber with a comparatively simple design that has a high system efficiency. To this end, the invention provides that a flow element is placed in the respective interior space while serving to effect a locally specific control of the flow of coolant.

摘要翻译： 本发明涉及一种燃气轮机的燃烧室，其中供应的燃料与供应的燃烧空气反应以产生工作介质。 燃烧室壁的内部设置有由多个隔热元件形成的衬里。 所述或每个隔热元件与燃烧室壁一起形成可以经受冷却剂作用的内部空间。 本发明的目的是提供具有较高系统效率的比较简单的燃烧室。 为此，本发明提供了流动元件放置在相应的内部空间中，同时用于实现对冷却剂流的局部特定控制。

公开(公告)号：US20050091987A1

公开(公告)日：2005-05-05

申请号：US10487519

申请日：2002-08-28

申请人： Peter Tiemann ,  Iris Oltmanns

发明人： Peter Tiemann ,  Iris Oltmanns

IPC分类号： F23R3/42 ,  F01D9/02 ,  F02C7/20

CPC分类号： F01D9/023 ,  Y02T50/675

摘要： This invention relates to a gas turbine having a combustion chamber arrangement and a turbine chamber connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of individual combustion chambers formed by input areas and transition areas converging in an annular gap leading to the turbine chamber and wherein the longitudinal axes of the individual combustion chambers are placed at an angle relative to an engine axis that is defined by the axial extension of the turbine chamber. In order to improve said gas turbine by visibly reducing the thermal and mechanical loads of the individual combustion chambers in the transition area so that cooling requirements can be lowered in said area, the transition area of at least one individual combustion chamber into the turbine chamber is deflected in the direction of the engine axis and substantially in the input area of the turbine chamber.

摘要翻译： 本发明涉及一种燃气轮机，其具有连接在所述燃烧室装置下游的燃烧室装置和涡轮室，其中燃烧室装置包括由输入区域和过渡区域形成的多个单独的燃烧室，该区域和过渡区域会聚在环形间隙中， 涡轮机室，并且其中各个燃烧室的纵向轴线相对于由涡轮机室的轴向延伸限定的发动机轴线成一定角度放置。 为了通过明显地减小过渡区域中的各个燃烧室的热和机械负荷来改善所述燃气轮机，从而可以在所述区域中降低冷却要求，至少一个单个燃烧室到涡轮机室的过渡区域是 在发动机轴线的方向和基本上在涡轮机室的输入区域中偏转。