EP2196628A1 - Support d'aube directrice - Google Patents

Support d'aube directrice Download PDF

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Publication number
EP2196628A1
EP2196628A1 EP08021446A EP08021446A EP2196628A1 EP 2196628 A1 EP2196628 A1 EP 2196628A1 EP 08021446 A EP08021446 A EP 08021446A EP 08021446 A EP08021446 A EP 08021446A EP 2196628 A1 EP2196628 A1 EP 2196628A1
Authority
EP
European Patent Office
Prior art keywords
volume
vane carrier
carrier
gas
guide
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Withdrawn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
EP08021446A
Other languages
German (de)
English (en)
Inventor
Roderich Bryk
Sascha Dr. Dungs
Martin Hartmann
Uwe Kahlstorf
Karl Dr. Klein
Oliver Dr. Lüsebrink
Mirko Milazar
Nicolas Savilius
Oliver Dr. Schneider
Shilun Dr. Sheng
Vadim Shevchenko
Gerhard Simon
Norbert Thamm
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 EP08021446A priority Critical patent/EP2196628A1/fr
Publication of EP2196628A1 publication Critical patent/EP2196628A1/fr
Withdrawn legal-status Critical Current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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C37/00—Cast-iron alloys
    • C22C37/04—Cast-iron alloys containing spheroidal graphite
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/11—Iron
    • F05D2300/111—Cast iron
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties

Definitions

  • the invention relates to a guide vane carrier, in particular for a gas or steam turbine, which is manufactured in a casting process. It further relates to a method of manufacturing a vane carrier.
  • Gas or steam turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel or superheated steam is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, wherein compressed air is supplied by an air compressor.
  • the steam turbine steam generated by a steam generator is supplied.
  • the working medium under high pressure and high temperature is then passed through a downstream turbine unit, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • For guiding the flow of the working medium in the turbine unit also commonly associated between adjacent blade rows with the turbine housing and combined into rows of guide vanes are arranged.
  • vanes are fixed in each case via a blade root, also referred to as a platform, on a guide vane carrier of the turbine unit.
  • this vane support is usually conical or cylindrical in shape and consists of an upper and a lower segment, the z. B. are interconnected via flanges.
  • the guide vane carrier or its upper and lower segment is often manufactured as a one-piece casting made of heat-resistant steel.
  • the cast steel allows a relatively simple production with good temperature resistance of the vane support.
  • the invention is based on the object of specifying a guide vane carrier and a method for producing a vane carrier, which, with particularly low production costs, permits a particularly good heat resistance and a particularly high degree of flexibility with regard to the choice of material.
  • the vane carrier is made of different materials by volume.
  • the invention is based on the consideration that a particularly good heat resistance of the guide blade carrier would be achieved if the comparatively strongly thermally loaded volume regions of the guide blade carrier would consist of a particularly temperature-resistant material such as heat-resistant steel. For large volume ranges of the vane carrier, the temperature resistance of such a high quality material is not required.
  • the guide vane carrier has a temperature profile which has comparatively small areas with high temperatures and a larger rear area with lower temperatures. High temperatures occur in the region of the entanglement of the vanes and the ring segments arranged between the vanes feet, since these components cause a local heat input in the region of their attachment. Based on the realization that a particularly heat-resistant material is not required outside of these areas, a reduction in production costs and a conservation of resources could be achieved by using a different material. This can be achieved by virtue of the fact that the guide vane carrier is made of different materials by volume.
  • the most temperature-resistant of the materials is arranged in a volume range provided for a higher thermal load. This ensures that the guide blade carrier can not be damaged by penetration of working fluid from the hot gas or steam channel or by direct heat input at the attachment points of the vanes, since then a corresponding temperature-resistant material such as heat-resistant steel is provided here. Conversely, this means that in areas designed for lower thermal stress, a less temperature-resistant material is used. This allows savings in terms of material costs.
  • the intended for a higher thermal load volume range is a hot gas duct and / or a combustion chamber facing portion of the vane support.
  • the highest temperatures occur at the outlet of the combustion chamber. Therefore, particularly temperature-resistant material should be arranged here in particular.
  • the region of the guide blade carrier facing the hot gas channel ie in the case of a cylindrical or conical guide blade carrier, is the one Inside, subjected to much higher temperatures than the outside. Therefore, particularly temperature-resistant materials should be used here.
  • the partially different materials of the vane carrier ideally already connect by pouring.
  • at least two volume regions are advantageously connected in a form-fitting manner. This can, for example, by introducing a corresponding contour in the areas, for example in the manner of a tongue and groove connection, a dovetail connection or the like. or additional connection segments e.g. be provided with appropriate connecting bolts between the areas. This ensures a particularly good cohesion of the different volume ranges of the vane carrier.
  • a volume range of the guide vane carrier made of cast iron with nodular graphite also called spheroidal graphite iron. It is an iron-carbon alloy with a carbon content higher than 2.06%. Unlike steel, carbon is precipitated in the form of non-metallic graphite.
  • spheroidal graphite cast iron has a lower thermal load than heat-resistant steel, it can be produced relatively inexpensively and is easy to process. In the case of a vane carrier consisting of regions of different materials, it can therefore be used in particular in the areas of the vane carrier designed for a lower thermal load, and thus a significantly more cost-effective production can be achieved without sacrificing the stability of the vane carrier.
  • the invention is achieved by casting a first region of the vane carrier from a first material, and then a second volume region of the vane carrier from a first volume region different material is poured into the first volume range.
  • the guide blade carrier is partially flexible adaptable to the different thermal loads in the interior of the gas turbine and it can be used in a lower thermal stress areas cheaper materials, while in higher thermally stressed areas find relatively high-quality materials application.
  • a secure connection of the different areas can be achieved directly during the casting.
  • the already explained measures such as an additional positive connection can be provided by corresponding introduced grooves.
  • such a vane carrier is used in a gas or steam turbine and such a gas or steam turbine in a gas and steam turbine power plant.
  • the advantages achieved by the invention are in particular that a flexible adaptation of the guide vane carrier to the temperature profile present in a gas or steam turbine is possible by the design of a guide vane with partially different materials, without losing the integral design of the vane carrier and its advantages over a Abandon construction with several axial segments.
  • the component is cost-optimized. The higher the thermal requirements for the gas or steam turbine rise, which is to be expected more and more in the future, the higher the cost savings through this method. Optimized use of the materials used also increases procurement flexibility.
  • FIG. 1 shows in detail a longitudinal section through a vane carrier 1.
  • the vane support 1 is usually conical or cylindrical in shape and consists of two segments, an upper and a lower segment, the z. B. are interconnected via flanges. Only the section through the upper segment is shown here.
  • the guide vane carrier 1 shown comprises a number of fastening elements 2 for the guide vanes and ring segments for sealing the hot gas channel.
  • the lower one, ie in Fig. 1 shown below area of the fasteners 2 is the hot gas or steam channel facing region of the vane support 1 and is therefore subjected to higher temperatures than the upper, ie in Fig. 1 area shown above.
  • the combustion chamber of the gas turbine is provided in the figure on the left side of the vane support 1, so that higher temperatures prevail here than in areas lying further to the right.
  • the vane support 1 is partially made of different materials.
  • a first volume region 4 which comprises the outflow-side end of the hot gas or steam channel and possibly the combustion chamber remote areas of the hot gas channel, which are acted upon by comparatively lower temperatures, the guide vane carrier is made of cast iron with nodular graphite or ductile iron. In these areas, a comparatively high-quality cast steel is not required, since lower temperatures prevail here.
  • the guide blade carrier 1 is made of heat-resistant cast steel in a second volume region 6.
  • This second volume region 6 is cast directly onto the first volume region 4, so that in this respect a dimensionally stable connection is formed.
  • the second volume region 6 is provided at the inlet end of the hot gas or steam channel.
  • the contours of the volume ranges can now be adapted to the temperature profile prevailing on the guide blade carrier 1.
  • the second volume region 6 which is made of heat-resistant cast steel, further extended in the direction away from the working medium inlet areas. This may be desirable at particularly high temperatures present in a gas turbine (a line 8 shows here later in FIG. 4 shown cross section).
  • FIG. 3 Another embodiment is in FIG. 3 shown.
  • form-fitting connections here in the form of dovetail connections 10
  • dovetail connections are provided between the volume regions.
  • connections for example in the manner of a tongue and groove connection be provided.
  • Corresponding recesses can for example be introduced after the casting of the first volume region 4 and are then filled directly during the casting of the second volume region 6.
  • FIG. 4 shows the guide blade carrier in cross-section, ie axial normal section, as shown by the line 8 in FIG. 2 marked.
  • the FIG. 4 shows that the higher volume material second volume region 6 is not continued into the areas of the flanges 12, with which the lower and upper segments of the vane support 1 are connected, but only the thermally highly loaded, inner part lined. Accordingly, the first volume region 4 is arranged outside.
  • FIG. 5 shows a further embodiment of the vane support 1.
  • GJS-400 ductile iron
  • G17CrMoV5-10 or GX12CrMoVNbN9-1 high-strength cast steel
  • an annular connecting part 14 is also provided between the volume regions, which produces a positive connection. This can be fastened, for example, with bolts on the cast steel of the second volume region 6.
  • FIG. 6 and 7 and FIGS. 8 and 9 show by way of example the step of the casting process of the vane carrier 1 FIG. 6 and 8th is first to see the first volume area 4 of a less heat-resistant material, which is poured in a rough contour. In this case, corresponding recesses for the second volume region 6 and other volume regions 16 left, in which a comparatively more heat-resistant material is poured.
  • FIG. 9 shows that it can be specifically addressed to the respective operating requirements in terms of heat resistance of the individual regions of the vane support 1 and possibly only small volume ranges of the highly heat-resistant and expensive material must be made, which allows a resource-saving and less expensive production of the vane support 1, without thereby having to compromise in terms of operational safety and durability, for example, a gas or steam turbine to accept.
  • a gas turbine 101 as in FIG. 10 has a compressor 102 for combustion air, a combustion chamber 104 and a turbine unit 106 for driving the compressor 102 and a generator, not shown, or a working machine.
  • the turbine unit 106 and the compressor 102 are arranged on a common turbine shaft 108, also referred to as turbine rotor, to which the generator or the working machine is also connected, and which is rotatably mounted about its central axis 109.
  • the combustor 104 which is in the form of an annular combustor, is equipped with a number of burners 110 for combustion of a liquid or gaseous fuel.
  • the turbine unit 106 has a number of rotatable blades 112 connected to the turbine shaft 108.
  • the blades 112 are annularly disposed on the turbine shaft 108 and thus form a number of blade rows.
  • the turbine unit 106 includes a number fixed stator vanes 114 also annularly attached to a vane support 1 of the turbine unit 106 to form rows of vanes.
  • the blades 112 serve to drive the turbine shaft 108 by momentum transfer from the turbine unit 106 flowing through the working medium M.
  • the vanes 114 serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 114 or a row of vanes and a ring of blades 112 or a blade row is also referred to as a turbine stage.
  • Each vane 114 has a platform 118 which is arranged to fix the respective vane 114 to a vane support 1 of the turbine unit 106 as a wall element.
  • the platform 118 is a thermally comparatively heavily loaded component, which forms the outer boundary of a hot gas channel for the turbine unit 106 flowing through the working medium M.
  • Each blade 112 is fastened to the turbine shaft 108 in an analogous manner via a platform 119, also referred to as a blade root.
  • a ring segment 121 is respectively arranged on a guide vane carrier 1 of the turbine unit 106.
  • the outer surface of each ring segment 121 is also exposed to the hot, the turbine unit 106 flowing through the working medium M and spaced in the radial direction from the outer end of the opposed blades 112 through a gap.
  • the arranged between adjacent rows of stator ring segments 121 serve in particular as cover that protect the inner housing in the guide blade carrier 1 or other housing-mounting components from thermal overload by the turbine 106 flowing through the hot working medium M.
  • the combustion chamber 104 is configured in the exemplary embodiment as a so-called annular combustion chamber, in which a plurality of burners 110 arranged around the turbine shaft 108 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 104 is configured in its entirety as an annular structure, which is positioned around the turbine shaft 108 around.
  • a significant cost reduction in the production of the gas turbine 101 or a steam turbine can be achieved with simultaneously high operational safety and service life.
  • the majority of the guide blade carrier 1 can be made of a much cheaper base material.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08021446A 2008-12-10 2008-12-10 Support d'aube directrice Withdrawn EP2196628A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08021446A EP2196628A1 (fr) 2008-12-10 2008-12-10 Support d'aube directrice

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08021446A EP2196628A1 (fr) 2008-12-10 2008-12-10 Support d'aube directrice

Publications (1)

Publication Number Publication Date
EP2196628A1 true EP2196628A1 (fr) 2010-06-16

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Family Applications (1)

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EP08021446A Withdrawn EP2196628A1 (fr) 2008-12-10 2008-12-10 Support d'aube directrice

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EP (1) EP2196628A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2644833A1 (fr) * 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
DE102014202744A1 (de) * 2014-02-14 2015-08-20 Siemens Aktiengesellschaft Schutz vor Erosion und Erosionskorrosion an Stegen von Gußgehäusen
EP3421727A1 (fr) * 2017-06-30 2019-01-02 Ansaldo Energia Switzerland AG Support d'aubes de turbine à gaz et turbine à gaz équipée d'un tel support d'aubes de turbine
FR3098849A1 (fr) * 2019-07-16 2021-01-22 Safran Aircraft Engines Carter amélioré de module d’aéronef
WO2023112669A1 (fr) * 2021-12-15 2023-06-22 三菱重工業株式会社 Turbine à vapeur

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60116805A (ja) * 1983-11-29 1985-06-24 Mitsubishi Heavy Ind Ltd 鋳込みによる仕切板の製作方法
JPS62267506A (ja) * 1986-05-15 1987-11-20 Toshiba Corp 蒸気タ−ビンのケ−シング
EP1033478A2 (fr) * 1999-03-02 2000-09-06 ABB Alstom Power (Schweiz) AG Boítier pour une turbomachine thermique
GB2412949A (en) * 2004-04-05 2005-10-12 Snecma Moteurs Turbine stator casing formed by hot isostatic compression
EP1865155A1 (fr) * 2006-06-06 2007-12-12 Siemens Aktiengesellschaft Carter de turbine à vapeur ou à gaz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60116805A (ja) * 1983-11-29 1985-06-24 Mitsubishi Heavy Ind Ltd 鋳込みによる仕切板の製作方法
JPS62267506A (ja) * 1986-05-15 1987-11-20 Toshiba Corp 蒸気タ−ビンのケ−シング
EP1033478A2 (fr) * 1999-03-02 2000-09-06 ABB Alstom Power (Schweiz) AG Boítier pour une turbomachine thermique
GB2412949A (en) * 2004-04-05 2005-10-12 Snecma Moteurs Turbine stator casing formed by hot isostatic compression
EP1865155A1 (fr) * 2006-06-06 2007-12-12 Siemens Aktiengesellschaft Carter de turbine à vapeur ou à gaz

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104220703B (zh) * 2012-03-26 2016-04-13 阿尔斯通技术有限公司 承载环
WO2013144040A1 (fr) * 2012-03-26 2013-10-03 Alstom Technology Ltd Bague de support
CN104220703A (zh) * 2012-03-26 2014-12-17 阿尔斯通技术有限公司 承载环
US20150082807A1 (en) * 2012-03-26 2015-03-26 Alstom Technology Ltd. Carrier ring
JP2015512485A (ja) * 2012-03-26 2015-04-27 アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ 支持リング
EP2644833A1 (fr) * 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
US10012094B2 (en) 2012-03-26 2018-07-03 Ansaldo Energia Switzerland AG Carrier ring
DE102014202744A1 (de) * 2014-02-14 2015-08-20 Siemens Aktiengesellschaft Schutz vor Erosion und Erosionskorrosion an Stegen von Gußgehäusen
EP3060766A1 (fr) * 2014-02-14 2016-08-31 Siemens Aktiengesellschaft Protection contre l'érosion et la corrosion par érosion de nervures de carter moulés
EP3421727A1 (fr) * 2017-06-30 2019-01-02 Ansaldo Energia Switzerland AG Support d'aubes de turbine à gaz et turbine à gaz équipée d'un tel support d'aubes de turbine
CN109209516A (zh) * 2017-06-30 2019-01-15 安萨尔多能源瑞士股份公司 燃气涡轮的涡轮导叶载体和包括涡轮导叶载体的燃气涡轮
FR3098849A1 (fr) * 2019-07-16 2021-01-22 Safran Aircraft Engines Carter amélioré de module d’aéronef
WO2023112669A1 (fr) * 2021-12-15 2023-06-22 三菱重工業株式会社 Turbine à vapeur

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