EP2236758A1 - Système d'aube avec plaques d'étanchéité comportant des nervures - Google Patents

Système d'aube avec plaques d'étanchéité comportant des nervures Download PDF

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Publication number
EP2236758A1
EP2236758A1 EP09004410A EP09004410A EP2236758A1 EP 2236758 A1 EP2236758 A1 EP 2236758A1 EP 09004410 A EP09004410 A EP 09004410A EP 09004410 A EP09004410 A EP 09004410A EP 2236758 A1 EP2236758 A1 EP 2236758A1
Authority
EP
European Patent Office
Prior art keywords
sealing plate
turbine
blade system
casting
sealing
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Withdrawn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
EP09004410A
Other languages
German (de)
English (en)
Inventor
Tobias Buchal
Sascha Dungs
Winfried Esser
Birgit Grüger
Oliver Lüsebrink
Mirko Milazar
Nicolas Savilius
Oliver Schneider
Peter Schröder
Waldemar Socha
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 EP09004410A priority Critical patent/EP2236758A1/fr
Publication of EP2236758A1 publication Critical patent/EP2236758A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/108—Installation of cores
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc

Definitions

  • the invention relates to a blade system, in particular for a gas turbine, with a number of annularly arranged on a turbine rotor blades, wherein a number of sealing plates is disposed on a side surface of the turbine disk, and a gas turbine with such a blade system. It further relates to a method of casting a sealing plate for such a blade system.
  • 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 blade rows, are arranged thereon.
  • a turbine disk is usually provided for each turbine stage, to which the blades are fastened by means of their blade root.
  • 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 designed 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 opens.
  • 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.
  • sealing plates are usually provided on the turbine disks, which are mounted circumferentially circularly on the turbine disk on the respective surfaces normal to the turbine axis. In this case, a number of sealing plates are usually provided on each side of the turbine disk. These overlap in a scale-like manner and usually have a sealing wing, which extends in such a way to the respective adjacent vane, that the penetration of hot working medium in the direction of the turbine shaft is avoided.
  • the sealing plates fulfill even more functions. On the one hand they form the axial fixation of the turbine blades by appropriate fasteners, on the other hand they not only seal the turbine disk against penetration of hot gas from the outside, but also avoid leakage of guided inside the turbine disk cooling air, which usually forwarded to the cooling of the turbine blades in selbige becomes.
  • Such sealing plates with integrated sealing wings are usually produced by vacuum investment casting (eg by lost-wax casting). In this case, a certain allowance must be provided in order to be able to compensate for process-related dimensional inaccuracies. Due to geometry - the sealing plates have wide, very thin areas and mass accumulations at other places - a delay and a certain porosity can not be avoided, especially in the thin areas under vacuum investment casting. Due to the requirement profile of the sealing plates, however, these are often made of alloys which can not be produced close to the final contour in a process other than the vacuum investment casting described.
  • the invention is therefore based on the object, a blade system and a method for casting a sealing plate indicate for a blade system, which allows for a maximum efficiency of a gas turbine simultaneously simplified construction.
  • the respective sealing plate has a web structure on one end face.
  • the invention is based on the consideration that a particularly simple construction of the blade system would be possible if the hitherto customary investment casting method with subsequent mechanical post-processing could be simplified.
  • the processing of the large end faces of the sealing plates is particularly complex, since a particularly flat surface for adequate sealing of the blade feet and outer areas of the turbine disk must be made here. A poor seal leads namely to loss of cooling air with a corresponding loss of efficiency.
  • the processing of the end faces of the sealing plates with good sealing should therefore be simplified by a number of raised webs is introduced to the end face, the sealing plate thus has a web structure on its front side.
  • the mechanical post-processing can namely be limited to the webs, since only these rest against the adjacent components. This allows a particularly simple construction of the blade system.
  • the web structure has a raised web in an edge region of the respective sealing plate and / or a depression in a central region of the sealing plate. This ensures - with appropriate mechanical post-processing - a good seal of the sealing plate at its edge regions, ie the edges, so that the sealing effect occurs over the entire surface. In the central, surrounded by the webs recessed areas then no further mechanical post-processing is required. These areas are made thinner and thus also allow material to be saved during construction the sealing plate, without affecting the operational effect.
  • a groove and / or a spring is advantageously arranged in the region of an edge of the respective sealing plate.
  • Such a tongue and groove connection has a better sealing effect compared to the usual simple overlapping of the sealing plates.
  • the object is achieved by casting a web structure into the sealing plate on one end face. This allows in addition to the advantages already described in precision casting better supply of thin, lying between the webs areas, which there can be avoided pores and optionally can be dispensed with the hot isostatic pressing.
  • sealing plates In order to avoid distortion of the wax models used in the vacuum investment casting, advantageously two equally shaped sealing plates are cast in a common casting mold.
  • the sealing plates should be arranged parallel.
  • Such a “sandwich construction" further ensures stabilization during casting and solidification.
  • mass inhomogeneities can be reduced and, associated with this, the heat balance can be made uniform, so that the solidification / dimensional stability can be better controlled and the porosity can be further reduced. This results in a particularly high material quality with simultaneous ease of manufacture of the sealing plate.
  • a casting core is introduced between the sealing plates. This serves to distance between the cast in a mold sealing plates and should be made of a ceramic material. This can be a particularly simple and inexpensive plate-shaped core structure can be selected, which further simplifies the production of the sealing plates.
  • a gas turbine comprises such a blade system and / or a blade system made by such a method.
  • a gas and steam turbine plant advantageously comprises such a gas turbine.
  • the advantages achieved by the invention are in particular that a particularly simple design and construction of the sealing plate is made possible by the attachment or the casting of a web structure on a sealing plate.
  • the production and material costs are particularly low. Due to the resulting thinner areas between the webs, the use of materials and the resulting costs can be reduced. A reworking of the large plane surfaces is not required in the web structure, only the webs themselves must be reworked, yet a particularly good sealing effect of the sealing plate is achieved during operation.
  • FIG. 1 shows a blade system 1 as a section through the outer periphery of a turbine shaft mounted turbine disk 6 of a blade stage of a gas turbine engine according to the prior art.
  • a blade 12 is arranged in a blade holding groove 30 with its blade root 32.
  • the blade root 32 of the blade 12 is fir-tree-shaped in cross-section and corresponds to the Christmas tree shape of the blade holding groove 30.
  • the schematic representation of the contour of the blade root 32 and the blade holding groove 30 is compared to the rest of the representation of FIG. 2 played rotated by 90 °.
  • the illustrated blade retaining groove 30 extends between the side surfaces 34 of the turbine disk 6.
  • Respectively adjacent guide vanes 36 are not shown in detail, which - viewed in the flow direction of the working medium of the gas turbine - upstream and downstream of the blade 12 are arranged.
  • the vanes 36 are arranged radially in wreaths.
  • sealing disks 40 are used circumferentially on each of the side walls 34 in a scale-like manner.
  • the sealing plates 40 also provide for an axial fixation of the blade root 32 in the blade retaining groove 30 and thus secure it against axial displacement.
  • the radial and azimuthal securing has already been achieved by the Christmas tree shape of the blade retaining groove 30.
  • the sealing plates 40 prevent leakage of cooling air channels 48 introduced through the turbine disk 36 into the blade root 32 and the rotor blade 12.
  • the sealing plate 40 is usually cast with a certain allowance. In this case, usually a vacuum investment casting method is used and then the sealing plates 40 are compacted after casting to eliminate porosity by means of hot isostatic pressing. Subsequently, a mechanical post-processing to bring the sealing plate 40 in its finished contour. Such a manufacturing process is relatively complicated and expensive. In order to simplify the manufacturing process for the sealing plate 40, the sealing plate 40 should therefore have a web structure 50, as in FIG FIG. 2 shown.
  • the web structure 50 of the sealing plate 40 on the turbine disk 6 facing end face comprises a plurality of webs 52, which are arranged in particular in the edge regions. To stabilize the sealing plate are still further webs 52 arranged. In the central region 54 of the sealing plate 40 remain recesses 56. By introducing the web structure 50 in the sealing plate 40 is a lesser material use at the same time good sealing between the sealing plate 40 and turbine disk 6 possible.
  • the webs 52 and the recess 56 is again in section in FIG. 3 shown.
  • the webs 52 in the upper and lower edge region of the sealing plate 40 allow the webs 52 a good seal.
  • the mechanical post-processing can be limited to the webs 52, since only these rest against the turbine disk 6.
  • the sealing plate 40 may also have not shown in detail grooves and / or springs on its edge, which allow a tongue and groove connection of adjacent sealing plates 40 in the circumferential direction of the turbine disk 6.
  • FIG. 4 and the FIG. 5 each show two sealing plates 40 which are arranged parallel to each other with an interposed casting core 58 made of a ceramic material.
  • two sealing plates 40 are simultaneously cast in a common casting mold.
  • FIG. 4 are facing in later operation of the turbine disk 6 end faces to the outside, ie turned to the mold, in the FIG. 5 in contrast, to the inside, ie to the casting core 58.
  • the image of the webs 52 takes place by introduced into the casting core 58 grooves 60th
  • the recesses 56 are fed particularly well in the casting process, whereby there pores can be avoided and can be dispensed with a downstream hot isostatic pressing.
  • the in 4 and 5 represented "sandwich" casting also contributes to the mechanical stability.
  • a gas turbine 101 as in FIG. 6 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 includes a blade system 1 having a number of rotatable blades 12 connected to the turbine shaft 108.
  • the blades 12 are arranged in a ring on the turbine shaft 108 and thus form a number of blade rows.
  • the turbine unit 106 includes a number of stationary vanes 36 which are also annularly attached to a vane support 110 of the turbine unit 106 to form rows of vanes.
  • the blades 12 serve to drive the turbine shaft 108 by momentum transfer from the turbine unit 106 flowing through the working medium M.
  • the vanes 36 serve to flow 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 36 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • each vane 36 has a blade root 118 which is arranged to fix the respective vane 36 to the vane support 110 of the turbine unit 106 as a wall member.
  • the blade root 118 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.
  • a ring segment 121 is disposed on a vane support 110 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 12 by 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 pad carrier 110 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09004410A 2009-03-26 2009-03-26 Système d'aube avec plaques d'étanchéité comportant des nervures Withdrawn EP2236758A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09004410A EP2236758A1 (fr) 2009-03-26 2009-03-26 Système d'aube avec plaques d'étanchéité comportant des nervures

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09004410A EP2236758A1 (fr) 2009-03-26 2009-03-26 Système d'aube avec plaques d'étanchéité comportant des nervures

Publications (1)

Publication Number Publication Date
EP2236758A1 true EP2236758A1 (fr) 2010-10-06

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EP09004410A Withdrawn EP2236758A1 (fr) 2009-03-26 2009-03-26 Système d'aube avec plaques d'étanchéité comportant des nervures

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016205921A1 (de) * 2016-04-08 2017-10-12 Siemens Aktiengesellschaft Rotorscheibenanordnung mit zweiteiliger Dichtung

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0801208A2 (fr) * 1996-04-12 1997-10-15 United Technologies Corporation Refroidissement pour ensemble rotor d'une turbine
US20050126736A1 (en) * 2002-11-14 2005-06-16 Rolls-Royce Plc Investment moulding process and apparatus
US20050249588A1 (en) * 2004-03-31 2005-11-10 Rolls-Royce Plc Seal assembly
US20070080505A1 (en) * 2005-10-06 2007-04-12 Siemens Power Generation, Inc. Seal plate for turbine rotor assembly between turbine blade and turbine vane
EP1944472A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'un rotor de turbine, élément d'étanchéité pour un rotor équipé d'aubes de rotor d'une turbine et rotor de turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0801208A2 (fr) * 1996-04-12 1997-10-15 United Technologies Corporation Refroidissement pour ensemble rotor d'une turbine
US20050126736A1 (en) * 2002-11-14 2005-06-16 Rolls-Royce Plc Investment moulding process and apparatus
US20050249588A1 (en) * 2004-03-31 2005-11-10 Rolls-Royce Plc Seal assembly
US20070080505A1 (en) * 2005-10-06 2007-04-12 Siemens Power Generation, Inc. Seal plate for turbine rotor assembly between turbine blade and turbine vane
EP1944472A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'un rotor de turbine, élément d'étanchéité pour un rotor équipé d'aubes de rotor d'une turbine et rotor de turbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016205921A1 (de) * 2016-04-08 2017-10-12 Siemens Aktiengesellschaft Rotorscheibenanordnung mit zweiteiliger Dichtung
DE102016205921B4 (de) 2016-04-08 2019-04-25 Siemens Aktiengesellschaft Rotorscheibenanordnung mit zweiteiliger Dichtung

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