EP1712745A1 - Komponente einer Dampfturbinenanlage, Dampfturbinenanlage, Verwendung und Herstellungsverfahren - Google Patents

Komponente einer Dampfturbinenanlage, Dampfturbinenanlage, Verwendung und Herstellungsverfahren Download PDF

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Publication number
EP1712745A1
EP1712745A1 EP05008207A EP05008207A EP1712745A1 EP 1712745 A1 EP1712745 A1 EP 1712745A1 EP 05008207 A EP05008207 A EP 05008207A EP 05008207 A EP05008207 A EP 05008207A EP 1712745 A1 EP1712745 A1 EP 1712745A1
Authority
EP
European Patent Office
Prior art keywords
component
layer
steam turbine
contour
ceramic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP05008207A
Other languages
German (de)
English (en)
French (fr)
Inventor
Detlef Dr. Haje
Dietmar Dr. Röttger
Friedhelm Schmitz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP05008207A priority Critical patent/EP1712745A1/de
Priority to CN2006800116707A priority patent/CN101155973B/zh
Priority to JP2008505854A priority patent/JP2008536050A/ja
Priority to PCT/EP2006/060664 priority patent/WO2006108746A1/de
Priority to US11/918,304 priority patent/US8137063B2/en
Priority to PL06708745T priority patent/PL1869292T3/pl
Priority to EP06708745A priority patent/EP1869292B1/de
Publication of EP1712745A1 publication Critical patent/EP1712745A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making
    • Y10T29/49245—Vane type or other rotary, e.g., fan

Definitions

  • the invention relates to a component of a steam turbine plant, for the application of superheated steam, with a hot steam space facing hot side, which has a contour and a fairing.
  • the invention further relates to a steam turbine plant, a use and a manufacturing method.
  • a steam turbine plant usually consists of the steam turbine as such and a steam turbine periphery.
  • the periphery serves to supply and remove superheated steam to and from the steam turbine.
  • the input-side periphery of the hot steam turbine is supplied at a high temperature and pressure to a turbine housing.
  • the superheated steam is first fed to an inflow region of the turbine, which essentially extends between a connection of a steam boiler to the turbine and the beginning of a blading in the housing or on the rotor of the turbine.
  • the superheated steam is conducted past the turbine blades as a working medium with cooling and expansion and in this way drives the rotor of the turbine while releasing its thermal and kinetic energy.
  • the rotation can be used to drive a generator and there to generate electrical power.
  • the relaxed and cooled working fluid may be in the form of cooled and relaxed vapor in the exit periphery, e.g. B. via a condenser, recirculate.
  • thermal insulation materials can usually be applied in layers of high thickness and would be well suited in principle.
  • a component eg. B. already due to the flow rate
  • said thermal insulation materials prove to be insufficient and already after a short time, z. B. by erosion, other abrasion and / or oxidation, destroyed and / or can be replaced.
  • This effect is reinforced by thermal shock stresses that make the materials brittle or at least create tensions. Dissipated thermal insulation materials then enter the flow of the working medium and can result in further enhancement of erosion damage in both the periphery and the turbine of the turbine plant.
  • the invention whose object is to provide a component of a steam turbine plant for exposure to superheated steam, a steam turbine plant and a use and a manufacturing method, according to the same thermal and mechanical resistance of the component, even at elevated temperature and pressure parameters a superheated steam, especially at temperatures above 600 ° C and / or pressures above 250 bar, is advantageously improved.
  • the cladding is arranged in the region of the hot side of the component and is formed by a number of shaped pieces adapted to the contour, wherein a shaped piece is in each case formed as a metal and ceramic component.
  • Composite layer is formed with at least one metal layer and at least one ceramic layer.
  • the invention is based on the consideration that, in principle, a physical separation of a surface of a component from a superheated hot steam space is advantageous, ie the invention is based on providing a contour of a hot side of the component facing a hot steam space with a cladding.
  • the invention has also recognized that due to the thickness of such a cladding, if these, in order to achieve increased efficiencies, at high pressure and temperature parameters, in particular> 600 ° C and / or> 250 Bar, a working medium is exposed to significant restrictions on the resistance of the component comes. With increasing thickness of a thermal insulation increases their thermal insulation effect, but it decreases in the manner explained above, their mechanical resistance, especially in thermal shock stress.
  • the thermal insulation effect decreases and increases the mechanical resistance under the influence of a working medium, which has a high flow rate and high reactivity due to high temperatures and high pressures.
  • the invention solves this conflict by the use of a lining in the form of a number of contour-adapted moldings which have a metal and ceramic composite layer on the hot side.
  • a greater layer thickness can be achieved.
  • the layers of the composite layer are advantageously cohesively, in particular intimately, connected to one another. But they can also be connected by methods such as screwing, plugging or riveting. That is, it can be for the case of a composite layer increase the thermal insulation effect of the cladding, without reducing the mechanical resistance.
  • the cladding according to the new concept proves to be particularly abrasion-resistant and erosion-resistant in a great variety of variants.
  • a shaped piece may preferably itself be curved, curved or bent such that it is z. B. fits perfectly to a contour and contour contoured in this sense. This can be advantageous in particular for small components. In particular, in the case of large components, a shaped piece itself may possibly be planar. Nevertheless, the fairing contour contoured be, for example, characterized in that at isolated points of the contour sufficiently small fittings are attached.
  • the cladding which according to the new concept provides for a combination of the two aspects mentioned above, avoids the above-described disadvantages of the prior art.
  • the mechanical, thermal and chemical stress on the hot side of the component is reduced by the cladding according to the new concept. This opens up the possibility to use current materials for higher working medium parameters or to use less expensive materials with the same parameters.
  • the ceramic layer may be closer to the hot side than the metal layer.
  • the metal layer serves as a holder, fixing and counter bearing of the ceramic layer. That is, practically, the metal layer within the composite layer serves as a supporting layer for the ceramic layer. This increases the mechanical resistance of the composite layer as a whole, especially at high mechanical stress in the context of increased working medium parameters. The metal layer recessed behind the ceramic layer is also exposed to less corrosion.
  • the metal layer may be closer to the hot side than the ceramic layer.
  • the metal layer within the composite layer serves primarily as an abrasion and / or erosion protection for the ceramic layer. That is, the ceramic layer is less mechanically stressed by the flow, especially at high flow parameters.
  • the advantages of the two aforementioned variants are combined by arranging the ceramic layer between an immediately adjacent first metal layer and second metal layer.
  • the support property of the first metal layer on the cold side is combined with an erosion-proof property of a second metal layer on the hot side.
  • the metal layer could also be arranged between an immediately adjacent first ceramic layer and the second ceramic layer.
  • the metal layer can serve as an inner support layer and is simultaneously protected by the ceramic layers against chemical and in particular corrosive stresses, in particular on the hot side.
  • the invention leads in particular to a steam turbine plant with a component of the kind explained above.
  • a component of the kind explained above use of the component as a conduit and / or collecting component in the context of a periphery of the steam turbine plant proves to be advantageous.
  • use of the component also proves to be advantageous in the case of a housing part, in particular in the inflow region of a steam turbine of a steam turbine plant.
  • the inflow can be understood in this context itself as a line component.
  • trim fitting with a metal and ceramic composite layer on a hot side in the rotor and blade area of a steam turbine.
  • FIG 1A shows a line component 10 in the form of a pipeline of a steam turbine periphery or in the inflow region of a steam turbine for acting on superheated steam, wherein the steam turbine is not shown in detail.
  • a component can for example be made of 9-12% Cr steel material.
  • the line component 10 has a hot steam space 1 facing hot side 3, which has a contour 5 and a panel 7.
  • the cladding 7 is formed in the form of a plurality of moldings 27 shown in FIG 3 on the contour 5, wherein the cladding in the FIG 1A shown in section and in Figure 3 as a perspective sectional view with respect to the fittings 27 is explained in more detail and shown.
  • Shaped piece 27 of the panel 7 is, as the section of the panel shows, adapted in its curved shape of the curved contour 5. That is, the shaped piece 27 is curved substantially like the contour 5 and extends parallel to the contour 5 and faces the hot side 3 of the line component 10.
  • the molding 27 has a metal and ceramic double composite layer 9, which is formed from exactly one metal layer 11 and exactly one ceramic layer 13. In particular, the metal layer 11 and the ceramic layer 13 are connected to one another in a materially cohesive manner.
  • the hot side 3 has the metal and ceramic composite layer 9 directly on the contour 5 of the component body 23 of the component 10.
  • the composite layer 9 is fixed mechanically as such on the contour 5. In the manufacturing process, this can be done for example by a dowel, screw or welded connection.
  • the panel 7 consists of the composite layer 9. It has namely have shown that in the periphery of steam turbines for the temperature range below 1000 ° C, a molding with a composite layer 9 can be formed with a thickness greater than 2 mm. This is a measure that goes well beyond conventional thermal barrier coatings, yet the composite 9 is thermally and mechanically extremely durable.
  • thermal barrier coatings in the form of a panel are plasma sprayed or vapor-deposited and can not be made for such a thickness - even if they do not have sufficient mechanical resistance, but which is possible in the context of the new concept by a corresponding fitting.
  • the erosion resistance is significantly improved by the fact that the metal layer 11 of the hot side 3 is closer than the ceramic layer 13. In addition, the metal layer 11 but also acts as an overhead support or fixation for the ceramic layer 13.
  • the metal layer is presently provided as a high temperature resistant sheet metal material available, for. Example in the form of a sheet of a nickel-based alloy or other age-resistant alloy, which are suitable to wear a ceramic layer. As part of a manufacturing process of the composite layer 9, this can be easily adhered to a ceramic layer 13 or otherwise mechanically fixed, so that at the boundary layer 15, an intimate connection is formed.
  • As a material for the ceramic layer in particular a ceramic with particularly low thermal conductivity, z. As a zirconia-based ceramic, proved to be particularly advantageous.
  • the ceramic layer serves for heat insulation.
  • a metal layer in the form of a sheet metal fitting can be pressed onto a first loose ceramic molding and hold the latter by a contact pressure on the contour.
  • a modification of this embodiment not shown here could also form a sandwich arrangement in the form of a metal-ceramic-metal composite layer. That is, in a modification of FIG 1A could be arranged on the back of the ceramic layer 13 and directly on the contour 5 a further metal layer in the form of a sheet metal layer for reinforcement. Such lying between the contour 5 and ceramic layer 13 sheet metal can be made in comparison to the illustrated metal layer 11 because of its lower temperature level in the operating case of a lower alloy sheet metal material, which has price advantages.
  • the hot side 3 directly facing sheet is made of a higher quality sheet metal.
  • FIG. 1B shows a similar, second embodiment of a line component 20 according to the concept of the invention, in which, moreover, the parts corresponding to FIG. 1A are provided with the same reference symbols and will not be explained again.
  • the ceramic layer 13 is closer to the hot side 3 than the metal layer 11. Both layers 11, 13 are connected to one another at the borderline 15 in a materially bonded or optionally only form-fitting manner ,
  • the hot side 3, the metal and ceramic composite layer 9 to form a clearance space 17 from the contour 5, ie, component body 23 and composite layer 9 are spaced from each other.
  • the clearance space 17 is formed in the form of a coolant supply 19 and hollow.
  • the cladding 7 is thus configured in addition to the composite layer 9 with a cooling jacket, which is formed by the coolant supply.
  • FIGS. 2A and 2B Another modification of the cooling jacket will be explained with reference to FIGS. 2A and 2B. In turn, features with substantially the same function are provided with the same reference numerals.
  • the ceramic layer 13 is formed as a thin heat-insulating layer on a metal layer 11. In this way, the heat input is limited by the superheated steam from the hot steam space 1 in the component body 23.
  • the metal and ceramic composite layer 9 is provided with holes 21.
  • the otherwise hollow distance space 17 serves as a coolant supply 19, wherein the coolant can escape through the bores 21 into the hot steam space 1 and thus forms a cooling boundary layer on it as a thermal insulating layer formed ceramic layer 13, which has an additional thermal insulation effect.
  • the bores 21 are arranged in the metal layer 11 and in the ceramic layer 13. Alternatively or additionally, the ceramic layer 13 may also have pores through which the cooling medium can escape into the hot steam space 1.
  • a line component 40 is shown a modification of the third embodiment shown in FIG. 2A.
  • the fourth embodiment of a conduit component 40 has a clearance space 40 which is filled with a porous and / or reticulated material 29. This can in particular a porous ceramic or a network of fiber material, for. Glass or metal fibers, be.
  • the retention system formed in this way in the clearance space 17 is advantageously somewhat yielding and otherwise supports the composite layer 9 in an advantageous manner.
  • the panel 7 is particularly resistant to mechanical shocks z. B. by occurring in particular at a line component thermal instabilities, eg. B. attenuated during transient operations.
  • a similar decoupling of component body 23 and molded piece 27 can also be achieved by the sandwich structure explained in greater detail in conjunction with FIGS. 1A, 1B.
  • an additional metal layer (not shown) between contour 5 and ceramic layer 13 can have the effect of an additional holder or fixing counter-layer. In this way, a direct connection of the composite layer 9 of the line component 10 to the component body 23 in a transient behavior, eg. As in thermal instabilities, damped.
  • All panels 7 are fixed in the embodiments 10, 20, 30, 40 by a welded joint 25 on the component body 23.
  • other types of connection such as screws, rivets, staples or pegs o. ⁇ . Be provided.
  • a net may be, for example, metallic and sintered in a ceramic layer 13. As a result, the fittings are networked together and held better.
  • the net may preferably be fastened to the contour 5.
  • FIG. 3 shows a perspective view of the line components 10, 20, 30, 40, in which the panel 7 in the form of a plurality of fittings 27 are formed on the contour 5.
  • Each of the shaped pieces 27 is adapted to the contour 5 in the region of the shaped piece 23.
  • the component body 23 of the line component 10, 20, 30, 40 is initially provided. Thereafter, the cladding 7 is applied by applying a plurality of moldings 27 forming the cladding 7, each providing a contour-matched molding 27, and corresponding to the contour of the contour 5 and with a metal and ceramic composite layer 9 to the hot side 3 directed towards.
  • a metal layer and a ceramic layer are joined to one another in a material or form-locking manner to form the composite layer.
  • the fittings 27 themselves are screwed as required, glued or welded as shown in connection with the preceding figures, by a welded joint 25 in the context of the manufacturing process.
  • the said joining processes prove to be advantageous, in particular, since they facilitate the assemblability of the shaped pieces 27 and improve their mechanical stability with respect to transient thermal processes.
  • the component 10, 20, 30, 40 faces a hot steam space 1 Hot side 3 a on a component body 23 applied cladding 7, which is the contour 5 of the component body 23 adapted.
  • the cladding 7 has a number of shaped pieces 27, and a shaped piece 27 has a metal and ceramic composite layer 9, which is formed from at least one metal layer 11 and at least one ceramic layer 13.
  • the ceramic layer 13 serves in particular as an insulating layer.
  • the metal layer 11 serves in particular as a support or to protect against abrasion and / or erosion.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)
EP05008207A 2005-04-14 2005-04-14 Komponente einer Dampfturbinenanlage, Dampfturbinenanlage, Verwendung und Herstellungsverfahren Withdrawn EP1712745A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP05008207A EP1712745A1 (de) 2005-04-14 2005-04-14 Komponente einer Dampfturbinenanlage, Dampfturbinenanlage, Verwendung und Herstellungsverfahren
CN2006800116707A CN101155973B (zh) 2005-04-14 2006-03-13 汽轮机装置的部件、汽轮机装置、使用和制造方法
JP2008505854A JP2008536050A (ja) 2005-04-14 2006-03-13 蒸気タービン設備の構成要素、蒸気タービン設備および蒸気タービン設備の構成要素の利用と製造方法
PCT/EP2006/060664 WO2006108746A1 (de) 2005-04-14 2006-03-13 Komponente einer dampfturbinenanlage, dampfturbinenanlage, verwendung und herstellungsverfahren
US11/918,304 US8137063B2 (en) 2005-04-14 2006-03-13 Component of a steam turbine plant, steam turbine plant, application, and production method
PL06708745T PL1869292T3 (pl) 2005-04-14 2006-03-13 Część składowa instalacji turbiny parowej, instalacja turbiny parowej, zastosowanie i sposób wytwarzania
EP06708745A EP1869292B1 (de) 2005-04-14 2006-03-13 Komponente einer dampfturbinenanlage, dampfturbinenanlage, verwendung und herstellungsverfahren

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05008207A EP1712745A1 (de) 2005-04-14 2005-04-14 Komponente einer Dampfturbinenanlage, Dampfturbinenanlage, Verwendung und Herstellungsverfahren

Publications (1)

Publication Number Publication Date
EP1712745A1 true EP1712745A1 (de) 2006-10-18

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP05008207A Withdrawn EP1712745A1 (de) 2005-04-14 2005-04-14 Komponente einer Dampfturbinenanlage, Dampfturbinenanlage, Verwendung und Herstellungsverfahren
EP06708745A Not-in-force EP1869292B1 (de) 2005-04-14 2006-03-13 Komponente einer dampfturbinenanlage, dampfturbinenanlage, verwendung und herstellungsverfahren

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP06708745A Not-in-force EP1869292B1 (de) 2005-04-14 2006-03-13 Komponente einer dampfturbinenanlage, dampfturbinenanlage, verwendung und herstellungsverfahren

Country Status (6)

Country Link
US (1) US8137063B2 (ja)
EP (2) EP1712745A1 (ja)
JP (1) JP2008536050A (ja)
CN (1) CN101155973B (ja)
PL (1) PL1869292T3 (ja)
WO (1) WO2006108746A1 (ja)

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EP2112334A1 (de) * 2008-04-21 2009-10-28 Siemens Aktiengesellschaft Außengehäuse für eine Strömungsmaschine
EP2161414A1 (en) 2008-09-09 2010-03-10 General Electric Company Steam turbine part including ceramic matrix composite (CMC)
WO2010054951A1 (de) * 2008-11-13 2010-05-20 Siemens Aktiengesellschaft Innengehäuse für eine strömungsmaschine
EP2696028A1 (en) * 2012-08-06 2014-02-12 Siemens Aktiengesellschaft A turbomachine component for hot gas path of a gas turbine
EP3599350A1 (de) * 2018-07-23 2020-01-29 Siemens Aktiengesellschaft Turbinengehäuse sowie verfahren zum herstellen eines turbinengehäuses

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EP2022951A1 (de) * 2007-08-08 2009-02-11 Siemens Aktiengesellschaft Verfahren zur Herstellung eines Turbinengehäuses sowie Turbinengehäuse
EP2224167A1 (de) * 2009-02-25 2010-09-01 Siemens Aktiengesellschaft Gehäuse einer Gasturbine
US20140119886A1 (en) * 2012-10-31 2014-05-01 General Electric Company Turbine cowling system
ITFI20130118A1 (it) * 2013-05-21 2014-11-22 Nuovo Pignone Srl "compressor with a thermal shield and methods of operation"
EP2871330A1 (de) * 2013-11-07 2015-05-13 Siemens Aktiengesellschaft Strömungsmaschine mit einer Beschichtung, Verwendung eines Kunststoffes zur Beschichtung und Verfahren zum Beschichten einer Strömungsmaschine

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* Cited by examiner, † Cited by third party
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EP2112334A1 (de) * 2008-04-21 2009-10-28 Siemens Aktiengesellschaft Außengehäuse für eine Strömungsmaschine
EP2161414A1 (en) 2008-09-09 2010-03-10 General Electric Company Steam turbine part including ceramic matrix composite (CMC)
WO2010054951A1 (de) * 2008-11-13 2010-05-20 Siemens Aktiengesellschaft Innengehäuse für eine strömungsmaschine
EP2696028A1 (en) * 2012-08-06 2014-02-12 Siemens Aktiengesellschaft A turbomachine component for hot gas path of a gas turbine
WO2014023687A1 (en) * 2012-08-06 2014-02-13 Siemens Aktiengesellschaft A turbomachine component for hot gas path of a gas turbine
EP3599350A1 (de) * 2018-07-23 2020-01-29 Siemens Aktiengesellschaft Turbinengehäuse sowie verfahren zum herstellen eines turbinengehäuses

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WO2006108746A1 (de) 2006-10-19
PL1869292T3 (pl) 2013-05-31
CN101155973A (zh) 2008-04-02
JP2008536050A (ja) 2008-09-04
US8137063B2 (en) 2012-03-20
CN101155973B (zh) 2010-05-19
EP1869292A1 (de) 2007-12-26
US20090041578A1 (en) 2009-02-12
EP1869292B1 (de) 2013-01-02

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