EP2218882A1 - Système de support d'aube directrice - Google Patents

Système de support d'aube directrice Download PDF

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Publication number
EP2218882A1
EP2218882A1 EP09002129A EP09002129A EP2218882A1 EP 2218882 A1 EP2218882 A1 EP 2218882A1 EP 09002129 A EP09002129 A EP 09002129A EP 09002129 A EP09002129 A EP 09002129A EP 2218882 A1 EP2218882 A1 EP 2218882A1
Authority
EP
European Patent Office
Prior art keywords
guide
vane
vane carrier
insulation
carrier system
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Withdrawn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
EP09002129A
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 EP09002129A priority Critical patent/EP2218882A1/fr
Publication of EP2218882A1 publication Critical patent/EP2218882A1/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Withdrawn legal-status Critical Current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
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • 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
    • F05D2300/5024—Heat conductivity

Definitions

  • the invention relates to a vane carrier system, in particular for a gas or steam turbine, with a vane carrier and a number of vanes and / or ring segments, wherein the respective vane and / or the respective ring segment comprises a hooking element, which is attached to the vane carrier. It further relates to a gas and / or steam turbine with such a Leitschaufelitatisystem.
  • 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.
  • the guide vanes are usually mounted in each case by means of a blade root, also referred to as a platform Interlocking elements fixed to a guide vane support 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 high durability and life of the vane support.
  • a cast steel production leads to relatively high production costs.
  • the invention is therefore based on the object to provide a guide vane support of the type mentioned above, which allows a particularly long service life and a particularly high flexibility in terms of material selection with particularly low production costs.
  • This object is achieved according to the invention by arranging an insulation element between the guide blade carrier and the hooking element.
  • the invention is based on the consideration that a particularly long service life of the guide vane carrier would be achievable if the heat input caused by the hot working medium into the vane carrier could be reduced. This would also allow a particularly great flexibility in terms of material selection, since a reduction of the heat input comparatively lower loadable materials could be used for the vane support, which would also mean a reduction of production costs.
  • the guide blade carrier has a temperature profile which has comparatively small regions with high temperatures and a larger rear region with lower temperatures.
  • High temperatures occur particularly in the region of the entanglement of the guide vanes and the ring segments arranged between the guide vanes feet, since these components cause a local heat input in the region of their attachment. Therefore, especially in this area, the heat conduction between the vane and ring segments and the vane support should be hindered to limit the temperature rise and thus provide a way to use a material with lower thermal property potential as a material for the vane support, which is associated with significant cost savings is.
  • This can be achieved by an insulating element being arranged between the guide blade carrier and the hooking element of the guide blade or of the ring segment of the preferably first and / or second turbine stage.
  • the respective insulation element should be formed to the respective Verhakungselement.
  • the insulation elements should be formed, for example, as sleeves, which can be set via the hooking elements on the blade root of the guide vanes or the ring segments.
  • the outer surfaces of the guide vane carrier and the channel walls are surrounded by cooling air extending radially through the vane carrier, and by the cooling air removed from the compressor. This results in a good cooling of the guide vane carrier, which can achieve a significant reduction in temperature in the temperature-critical areas of the vane carrier in the long term in connection with the proposed isolation measure.
  • the respective isolation element in an advantageous embodiment, an insulation plate, d. H. in its geometrical configuration disc-like flat and without any special folds.
  • Such an insulation plate can be produced particularly easily separately and requires only simple modifications to the hooking element or the fastening elements of the guide blade carrier. As a result, a particularly simple introduction of such insulation elements in the guide vane support system is possible.
  • the material for the insulation elements should be selected according to the operational requirements.
  • the respective insulation element should advantageously be made of the same material as the respective guide blade or advantageously of the same material as the respective guide blade carrier.
  • the respective insulation segment should advantageously be made of steel. This one has a special high heat resistance and is therefore particularly suitable for use in the thermally heavily loaded areas of Leitschaufelverhakung.
  • the thermal insulation of the insulating element while the heat-conducting cross-sectional area of the insulating element should be reduced.
  • a number of cavities are introduced into the respective insulation element. These should be introduced, for example in the form of holes perpendicular to the heat conduction direction and thus reduce the thermal conductivity of the insulation element.
  • the cavities are furthermore suitable for flowing through the cooling air available in the region of the guide blade carrier, as a result of which the effect of the insulation elements is further optimized.
  • the insulating element is made of ceramic.
  • Ceramic materials have a particularly low thermal conductivity and are therefore particularly suitable as insulators. Due to the low thermal conductivity can also be dispensed with cavities, which is why such ceramic materials allow a particularly simple production of insulation plates or other insulation elements.
  • such a guide vane system is part of a gas or steam turbine.
  • a gas and / or steam turbine are / is advantageously part of a gas and steam turbine plant.
  • the advantages achieved by the invention are in particular that is reduced by the introduction of an insulation segment in the area between vanes or ring segments and vane support the heat transfer from the hot working medium on the Verhakungs institute in the vane support and so a heating of the vane support is reduced.
  • This makes it possible to use a simple material for the vane carrier and consequently material costs and reduce component costs.
  • the use of cost-intensive high-temperature materials can be reduced or an increase in the gas inlet temperature in the turbine is made possible. This also allows a higher efficiency of the gas and steam turbine.
  • the vane carrier system 1 comprises a guide blade carrier 2, which comprises a number of fastening elements 4, to which guide vanes 6, which are combined into rows of guide vanes, and ring segments 8, which are combined into rotor blade rows, are fastened. In each case only one vane 6 and blade 7 of each row is shown in half section.
  • the guide vanes 6 comprise on their blade root 9 and the ring segments 8 interlocking elements 10, which form a positive connection with the fastening elements 4 of the guide blade carrier 2 and thus ensure the stabilization and secure retention of the guide vanes 6 and the ring segments 8 on the guide vane carrier 2.
  • cavities 12 are arranged between the guide vanes 6 or ring segments 8 and the guide blade carrier 2, in each case between the fastening elements, into which cooling air can be introduced from outside. Between the blade roots 9 of the guide vanes 6 and the ring segments 8 sealing plates 14 are attached, so that even here a penetration of hot working medium can be avoided.
  • FIG. 2 shows an insulation segment 16, which is integrally formed on the interlocking element 10 and is inserted in the manner of a sleeve on the interlocking element 10.
  • the insulation element 16 can also be designed as a simple insulation plate. Such an arrangement is in FIG. 3 shown. Again, the insulation plate is molded to the interlocking element 10 and can be relatively easily finished by its simple geometric shape.
  • the insulation element 16 can be made of different materials.
  • a ceramic material can be used which has a particularly low thermal conductivity.
  • Such an insulation element 16 is in FIG. 4 shown.
  • the ceramic material allows easy production in a flat parallelepiped shape and reduces the heat input into the guide blade carrier 2 by its low thermal conductivity.
  • the insulating member 16 may also be made of the same material as the respective vane carrier or the respective vane.
  • the insulation element 16 may also be made of steel.
  • a number of cavities 18, for example in the form of bores, should then be introduced into the respective insulation element 16, as in FIG FIG. 5 shown.
  • the cavities reduce the heat-conducting cross-sectional area and, with further cooling demand, the cooling air present in the area of the guide blade carrier 2 can flow through it, thus ensuring even better insulation of the guide blade carrier 2 against the temperatures of the hot working medium.
  • the vane carrier 2 By reducing the heat input into the vane carrier 2, it is possible to manufacture the vane carrier 2 from a comparatively less heat-resistant and expensive material, which allows a resource-saving, less expensive production of the vane carrier 2 and the vane carrier system 1, without sacrificing operational safety and lifetime, for example to have to accept a gas or steam turbine.
  • a gas turbine 101 as in FIG. 6 has a compressor 102 for combustion air, a combustion chamber 104 and a turbine unit 106.
  • 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 7 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 vane system 1 having a number of stationary vanes 6, which are also secured in a donut-like fashion to form vane rows on the vane support 2 of the turbine unit 106.
  • the blades 7 serve to drive the turbine shaft 108 by momentum transfer from the turbine unit 106 flowing through the working medium M.
  • the vanes 6, however, 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 6 or a row of vanes and a ring of blades 7 or a blade row is also referred to as a turbine stage.
  • FIG. 6 shows in a larger context, the blade root 9 of the vanes 6, for fixing the respective vane 6 on the vane support 2 of the turbine unit 106 is used.
  • the blade root 9 is a thermally comparatively heavily loaded component that forms the outer boundary of a hot gas channel for the turbine unit 106 flowing through the working medium M.
  • Each blade 7 is attached in a similar manner via a blade root 119 to the turbine shaft 108.
  • each ring segment 8 is arranged between the spaced blade roots of the vanes 6 of two adjacent rows of vanes on the guide blade carrier 2 of the turbine unit 106.
  • the outer surface of each ring segment 8 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 7 through a gap.
  • the ring segments 8 arranged between adjacent guide blade rows serve in particular as cover elements which protect the inner housing in the guide blade carrier 2 or other housing built-in components against thermal overstress by the hot working medium M flowing through the turbine 106.
  • 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.
  • the heat transfer from the acted upon with the hot working medium M blade roots 9 and ring segments 8 in the vane support 2 can be significantly reduced. This can be a significant cost reduction in the production of the gas turbine 101 or a steam turbine at the same time high operational safety and Lifespan can be achieved.
  • the heat input in the guide vane 2 this can namely be made of a much cheaper base material.
  • the temperature of the working medium M can be increased, which has an increase in the efficiency of the gas or steam turbine result.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09002129A 2009-02-16 2009-02-16 Système de support d'aube directrice Withdrawn EP2218882A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09002129A EP2218882A1 (fr) 2009-02-16 2009-02-16 Système de support d'aube directrice

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09002129A EP2218882A1 (fr) 2009-02-16 2009-02-16 Système de support d'aube directrice

Publications (1)

Publication Number Publication Date
EP2218882A1 true EP2218882A1 (fr) 2010-08-18

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ID=41016773

Family Applications (1)

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EP09002129A Withdrawn EP2218882A1 (fr) 2009-02-16 2009-02-16 Système de support d'aube directrice

Country Status (1)

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EP (1) EP2218882A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2961850A1 (fr) * 2010-06-28 2011-12-30 Snecma Turbine pour une turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
DE102013205883A1 (de) * 2013-04-03 2014-10-09 MTU Aero Engines AG Leitschaufelsegment mit integrierter Hitzeisolierung
US20170159494A1 (en) * 2015-12-07 2017-06-08 General Electric Company Steam turbine nozzle segment with complete sidewall and integrated hook design
CN111512021A (zh) * 2017-12-05 2020-08-07 赛峰飞机发动机公司 涡轮机涡轮的陶瓷基复合材料定子扇区与金属支撑件之间的连接

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841787A (en) * 1973-09-05 1974-10-15 Westinghouse Electric Corp Axial flow turbine structure
GB2119452A (en) * 1982-04-27 1983-11-16 Rolls Royce Shroud assemblies for axial flow turbomachine rotors
US5197853A (en) * 1991-08-28 1993-03-30 General Electric Company Airtight shroud support rail and method for assembling in turbine engine
WO1998049427A1 (fr) * 1997-04-28 1998-11-05 Siemens Aktiengesellschaft Dispositif d'isolation thermique pour une turbine a vapeur
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
GB2344140A (en) * 1998-09-28 2000-05-31 Gen Electric Inner shroud assembly for turbines/compressors
WO2008081485A1 (fr) * 2007-01-04 2008-07-10 Ansaldo Energia S.P.A. Ensemble d'aube fixe très résistante à la corrosion pour une turbine à vapeur, en particulier une turbine géothermique à impulsion

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841787A (en) * 1973-09-05 1974-10-15 Westinghouse Electric Corp Axial flow turbine structure
GB2119452A (en) * 1982-04-27 1983-11-16 Rolls Royce Shroud assemblies for axial flow turbomachine rotors
US5197853A (en) * 1991-08-28 1993-03-30 General Electric Company Airtight shroud support rail and method for assembling in turbine engine
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
WO1998049427A1 (fr) * 1997-04-28 1998-11-05 Siemens Aktiengesellschaft Dispositif d'isolation thermique pour une turbine a vapeur
GB2344140A (en) * 1998-09-28 2000-05-31 Gen Electric Inner shroud assembly for turbines/compressors
WO2008081485A1 (fr) * 2007-01-04 2008-07-10 Ansaldo Energia S.P.A. Ensemble d'aube fixe très résistante à la corrosion pour une turbine à vapeur, en particulier une turbine géothermique à impulsion

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2961850A1 (fr) * 2010-06-28 2011-12-30 Snecma Turbine pour une turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
DE102013205883A1 (de) * 2013-04-03 2014-10-09 MTU Aero Engines AG Leitschaufelsegment mit integrierter Hitzeisolierung
DE102013205883B4 (de) * 2013-04-03 2020-04-23 MTU Aero Engines AG Anordnung aus Leitschaufelsegmenten und Verfahren zur Herstellung einer derartigen Anordnung
US20170159494A1 (en) * 2015-12-07 2017-06-08 General Electric Company Steam turbine nozzle segment with complete sidewall and integrated hook design
CN111512021A (zh) * 2017-12-05 2020-08-07 赛峰飞机发动机公司 涡轮机涡轮的陶瓷基复合材料定子扇区与金属支撑件之间的连接

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