EP2184449A1 - Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice - Google Patents

Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice Download PDF

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Publication number
EP2184449A1
EP2184449A1 EP08019363A EP08019363A EP2184449A1 EP 2184449 A1 EP2184449 A1 EP 2184449A1 EP 08019363 A EP08019363 A EP 08019363A EP 08019363 A EP08019363 A EP 08019363A EP 2184449 A1 EP2184449 A1 EP 2184449A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
gas
turbine
metal foam
gas turbine
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Withdrawn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
EP08019363A
Other languages
German (de)
English (en)
Inventor
Roderick 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 EP08019363A priority Critical patent/EP2184449A1/fr
Publication of EP2184449A1 publication Critical patent/EP2184449A1/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Withdrawn legal-status Critical Current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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam

Definitions

  • the invention relates to a guide vane carrier, in particular for a gas turbine, which consists of a number of axial segments.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, 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 combustion chamber of the gas turbine may be embodied as a so-called annular combustion chamber, in which a plurality of circumferentially arranged around the turbine shaft burners in a common, surrounded by a high temperature resistant surrounding wall combustion chamber space.
  • the combustion chamber is designed in its entirety as an annular structure.
  • a single combustion chamber can also be provided a plurality of combustion chambers.
  • first row of guide vanes of a turbine unit which, together with the blade row immediately downstream in the flow direction of the working medium, forms a first turbine stage of the turbine unit, which is usually followed by further turbine stages.
  • the 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.
  • the guide blade carrier for securing the platforms of the guide vanes comprise an insulation segment.
  • a guide ring on the guide vane support of the turbine unit is arranged in each case.
  • Such a guide ring is spaced by a radial gap of the blade tips of the fixed at the same axial position on the turbine shaft blades of the associated blade row.
  • the guide vane carrier of the gas turbine usually made of cast steel. This is suitable to withstand the high temperatures within the gas turbine and it can thus ensure safe operation of the gas turbine.
  • the guide vanes of the gas turbine can either be fastened to a common guide vane carrier or separate axial segments are provided for each turbine stage.
  • the turbine vane carrier is exposed to extremely high temperatures, so that to avoid material damage sufficient cooling must be provided.
  • the invention is therefore based on the object to provide a guide vane, which allows a technically simpler design while maintaining operational safety and reaches a longer life.
  • At least one axial segment comprises a metal foam.
  • the invention is based on the consideration that a longer service life of the guide blade carrier would be achieved by a reliable and improved cooling of particular individual axial segments of the guide blade carrier. This could be achieved by choosing a more coolable material for the vane carrier. However, the areas that are exposed to the highest temperatures (eg near the compressor outlet or in the area of the entanglement of the guide vanes and the ring segments) should continue to be made of cast steel in order to withstand the prevailing temperatures. In those areas that are exposed to comparatively lower temperatures However, another material could be used for the respective axial segments.
  • the axial segments should not be made massive in low temperature areas, d. H. in particular have a lower density.
  • the material to be used should also have good strength and rigidity in order to be able to withstand the mechanical stresses inside a gas turbine. These properties has a metal foam. Therefore, at least one axial segment should comprise a metal foam.
  • the respective axial segment advantageously comprises stiffening beams and / or tubes. These beams can be welded in the manufacturing process between the massively designed axial segments and thus ensure a particularly good strength of the basic construction. The metal foam can then be introduced in a further manufacturing step in the spaces around the beams or pipes around.
  • the respective metal foam is open-pored, d. H. it has a comparatively high open porosity. This means that a comparatively large number of cavities are connected to each other and to the outside area. As a result, a particularly good cooling of the guide vane carrier is possible.
  • the respective metal foam for the flow is designed with a cooling medium, for example air.
  • a cooling medium for example air.
  • effusion cooling of the guide vane carrier is possible.
  • the cooling medium flows through the porous metal foam. This heats up the cooling medium.
  • the cooling medium is deflected by the hot gas of the combustion chamber in the main flow direction. This also forms a cooling film between porous wall and hot gas. This is now able to absorb heat and transported away in the flow direction. Thus, you can keep the wall temperature low.
  • Another advantage is the low pressure loss of the cooling system and the exact metering.
  • the thickness and porosity of the respective metal foam are adapted to the intended during operation local thermal and mechanical loads. Such an adjustment ensures precise matching of the metal foam by precise metering of the amount of cooling medium to the respective local temperature conditions and adaptation of strength and stability to the mechanical requirements.
  • the advantages associated with the invention are, in particular, that a technically much simpler and more cost-effective construction of a vane carrier and thus the entire gas turbine by a comparison with a massive structure significantly reduced weight is possible by the introduction of a metal foam in axial segments of a vane carrier.
  • the guide vane carrier is better cooled by cooling air and can thus even with the highest demands on the thermal load, ie highest gas turbine inlet temperatures are still performed with simple metallic materials.
  • Such better cooling in conjunction with the strength and symmetry of the metal foam, through which the structure is not weakened by stretching and distortion and local holes, has a lower axial and possibly also radial thermal expansion result.
  • the minimum gaps required to compensate for the thermal expansion can be made smaller, resulting in a higher turbine efficiency result.
  • FIG. 1 shows in detail a longitudinal section through a guide vane carrier 1.
  • the guide vane carrier 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.
  • the guide vane carrier 1 shown comprises a number of axial segments 24.
  • a metal foam 26 introduced in a part of the axial segments 24 of the vane support 1, a metal foam 26 introduced.
  • 26 stiffening bars 28 are introduced to increase the rigidity in the axial segments 24 with metal foam.
  • the remaining axial segments 24 are formed as castings 30 which are partially welded to the stiffening bars 28.
  • the metal foam 26 is adapted in its thickness and porosity in each case to the thermal and mechanical loads in the interior of the gas turbine. This ensures optimum matching of the material.
  • the metal foam 26 is open-pored, so that its cooling air supply and the cooling of the entire guide blade carrier 1 can be carried out by effusion cooling. Cooling air then flows through the open pores of the metal foam 26.
  • the gas turbine 101 includes 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 of stationary vanes 114, which are also attached in a donut-like manner 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 18 is a thermally comparatively heavily loaded component that forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 106.
  • 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 guide ring 121 is arranged on a guide blade carrier 1 of the turbine unit 6.
  • the outer surface of each guide ring 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 blades lying opposite him 112 through a gap.
  • the guide rings 121 arranged between adjacent rows of guide blades serve in particular as cover elements which protect the inner housing in the guide blade carrier 1 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08019363A 2008-11-05 2008-11-05 Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice Withdrawn EP2184449A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08019363A EP2184449A1 (fr) 2008-11-05 2008-11-05 Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08019363A EP2184449A1 (fr) 2008-11-05 2008-11-05 Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice

Publications (1)

Publication Number Publication Date
EP2184449A1 true EP2184449A1 (fr) 2010-05-12

Family

ID=40527417

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08019363A Withdrawn EP2184449A1 (fr) 2008-11-05 2008-11-05 Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice

Country Status (1)

Country Link
EP (1) EP2184449A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011014292A1 (de) * 2011-03-17 2012-09-20 Rolls-Royce Deutschland Ltd & Co Kg Zwischenstufendichtungsring sowie Verfahren zu dessen Herstellung

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1344895A2 (fr) * 2002-03-15 2003-09-17 ROLLS-ROYCE plc Boítier de turbomachine en matériau cellulaire
US20040141837A1 (en) * 2003-01-16 2004-07-22 Mcmillan Alison J. Gas turbine engine blade containment assembly
US20050111966A1 (en) * 2003-11-26 2005-05-26 Metheny Alfred P. Construction of static structures for gas turbine engines
WO2005061855A1 (fr) * 2003-12-20 2005-07-07 Mtu Aero Engines Gmbh Composant de turbine a gaz
EP1645347A1 (fr) * 2000-05-17 2006-04-12 Alstom Technology Ltd Procédé de fabrication d'une pièce moulée à charge thermique élevée
EP1726788A2 (fr) * 2005-05-24 2006-11-29 Rolls-Royce plc Assemblage pour la rétention d'aube de rotor d'un moteur de turbine à gaz
EP1878876A2 (fr) * 2006-07-11 2008-01-16 Rolls-Royce plc Joint abradable pour turbine à gaz et sa méthode de production

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1645347A1 (fr) * 2000-05-17 2006-04-12 Alstom Technology Ltd Procédé de fabrication d'une pièce moulée à charge thermique élevée
EP1344895A2 (fr) * 2002-03-15 2003-09-17 ROLLS-ROYCE plc Boítier de turbomachine en matériau cellulaire
US20040141837A1 (en) * 2003-01-16 2004-07-22 Mcmillan Alison J. Gas turbine engine blade containment assembly
US20050111966A1 (en) * 2003-11-26 2005-05-26 Metheny Alfred P. Construction of static structures for gas turbine engines
WO2005061855A1 (fr) * 2003-12-20 2005-07-07 Mtu Aero Engines Gmbh Composant de turbine a gaz
EP1726788A2 (fr) * 2005-05-24 2006-11-29 Rolls-Royce plc Assemblage pour la rétention d'aube de rotor d'un moteur de turbine à gaz
EP1878876A2 (fr) * 2006-07-11 2008-01-16 Rolls-Royce plc Joint abradable pour turbine à gaz et sa méthode de production

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011014292A1 (de) * 2011-03-17 2012-09-20 Rolls-Royce Deutschland Ltd & Co Kg Zwischenstufendichtungsring sowie Verfahren zu dessen Herstellung

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