EP1180196B1 - Turbomachine comportant un systeme d'etancheite pour un rotor - Google Patents

Turbomachine comportant un systeme d'etancheite pour un rotor Download PDF

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Publication number
EP1180196B1
EP1180196B1 EP00925282A EP00925282A EP1180196B1 EP 1180196 B1 EP1180196 B1 EP 1180196B1 EP 00925282 A EP00925282 A EP 00925282A EP 00925282 A EP00925282 A EP 00925282A EP 1180196 B1 EP1180196 B1 EP 1180196B1
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EP
European Patent Office
Prior art keywords
sealing
blade
sealing element
rotor
circumferential
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.)
Expired - Lifetime
Application number
EP00925282A
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German (de)
English (en)
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EP1180196A1 (fr
Inventor
Peter Tiemann
Michael Strassberger
Arnd Reichert
Dirk Lieser
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
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Siemens AG
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Publication date
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Priority to EP00925282A priority Critical patent/EP1180196B1/fr
Publication of EP1180196A1 publication Critical patent/EP1180196A1/fr
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Publication of EP1180196B1 publication Critical patent/EP1180196B1/fr
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • the invention relates to a turbomachine with a Sealing system for a rotor extending along a rotation axis extends, wherein the rotor is a first blade and one to the first blade in the circumferential direction of the rotor has adjacent second blade.
  • Rotatable blades of turbomachinery are in different Embodiments over the full circumference of the peripheral surface a rotor shaft, e.g. formed by a running disk is attached.
  • a blade usually has an airfoil, a paddle platform and a Shovel foot with a mounting structure on which from a correspondingly complementarily configured recess, made for example as a circumferential groove or axial groove is suitably received on the peripheral surface of the rotor shaft is fixed, and in this way the blade.
  • Constructive are after the insertion of the blades in the rotor shaft through the respective adjacent areas Gap formed in the operation of a turbine occasion Leakage flow of coolant or a rotor driving the give hot action fluids.
  • Such columns occur, for example between two adjoining paddle platforms circumferentially adjacent blades and between the peripheral surface of the rotor shaft and a radial on the peripheral surface adjacent blade platform.
  • Coolant e.g. of cooling air
  • FR 2 603 333 discloses a securing and sealing device known for the blades of a compressor.
  • a groove with Undercuts provided which at least partially each blade holding groove extending transversely to the peripheral surface of the rotor disk cuts.
  • a fuse element for hooking with each blade in the circumferential direction insertable.
  • a blade has the partially inserted into the groove securing element a Opening up, through the one on the front side of the blade root arranged nose can be inserted. After assembly the blade becomes the securing element in the circumferential direction shifted, so that this engages the nose and the blade secures against axial displacement. Consequently can successively inserted each blade in their respective retaining groove and secured.
  • For axial sealing is a second, parallel to the fuse element fitting sealing element arranged in the on the front side of the rotor disk Groove inserted.
  • US Patent 5,599,170 is a sealing concept for a blade of a gas turbine described. Divided by two adjacent adjacent blades, which in a rotatable about an axis running disk on the peripheral surface of Running disk are attached, one is essentially radially extending gap and a substantially axially extending gap formed. A sealing element seals the radial and at the same time the axial gap. The sealing element is used for this purpose in a cavity which through the Vane platforms of the blades is formed.
  • the Sealing element has a first and a second sealing surface on, which is adjacent to the axial or radial gap.
  • the Sealing element also has a thrust surface, which is extends obliquely to the radial direction.
  • the sealing effect is due to the due to the rotation of the running disk on the movable reaction element achieved centrifugal forces.
  • the reaction element transmits to the oblique thrust surface a force whose causes radially directed force component on the sealing element, that the first sealing surface seals the axial gap, during the axially directed force component on the sealing element causes the second sealing surface to the radial Gap seals.
  • the invention is based on the object for a turbomachine with one extending along a rotation axis Rotor, a first blade and a circumferential direction of the rotor adjacent to the first blade second blade has to indicate a sealing system.
  • the sealing system should in particular a particularly effective Limitation of possible leakage currents through gap areas and ensure clearances of the rotor, and opposite the occurring thermal and mechanical loads resistant be.
  • a turbomachine with one extending along a rotation axis
  • Rotor comprising a peripheral surface passing through the outer radial boundary surface of the rotor (25) is defined, in the plurality of receiving structures and a first blade and a second blade, each having a blade root and a blade platform adjacent the blade root is arranged, wherein the blade root of the first blade and the blade root of the second blade into the receiving structure are used, so that the blade platform of the first blade and the blade platform of the second Blade together, and so that between the Vane platforms and the peripheral surface a gap and a sealing system on the peripheral surface in the space is provided, wherein the sealing system is a circumferentially having extending sealing element, which a first partial sealing element and a second partial sealing element comprising, wherein the first partial sealing element and the second Part sealing element interlock, and wherein the partial sealing elements relative to each other in the circumferential direction movable are.
  • the invention is based on the consideration that during operation of a Turbomachine The rotor a flowing hot action fluid is exposed.
  • the hot action fluid does as a result of expansion work on the blades and offset this in rotation about the axis of rotation. Therefore, the Rotor with the blades both thermally and mechanically, especially due to the rotation occurring Centrifugal forces, very heavily loaded.
  • a coolant e.g. Cooling air
  • Coolant feeds is supplied to the rotor. It can both leakage flows of coolant and hot action fluid - So-called gap losses occur in the gap.
  • a gap is formed by the peripheral surface, here by the outer radial boundary surface the rotor is defined, as well as by the radial outwardly of the peripheral surface arranged respective platforms of two adjacent in the circumferential direction of the rotor arranged blades.
  • These leakage currents affect each other very detrimental to the cooling efficiency as well as the mechanical Installation resistance (smoothness and creep strength) of Blades in the receiving structure of the peripheral surface.
  • leakage currents which along the axis of rotation (axial leakage flows), for example, along the peripheral surface, oriented are.
  • leakage currents are vertical to the axis of rotation (radial leakage flows) along a Radial direction and thus substantially perpendicular to Peripheral surface are addressed, note.
  • An essential advantage over conventional sealing concepts results from the arrangement of the sealing system on the peripheral surface. This makes it possible that the sealing system directly adjacent to the peripheral surface and a sealing effect is made. This is to prevent leakage currents particularly good in the axial direction along the peripheral surface suitable. For example, already the entry of one hot action fluid, e.g. the hot gas in a gas turbine, largely suppressed in the space, and an axial directed flow in the space along the peripheral surface significantly reduced. This protects the material of the rotor, in particular the material of the blade platforms, in front of the high temperatures and the possible oxidizing and corrosive Influences of the hot action fluid.
  • the sealing system can be dimensioned in the radial direction so that it directly adjacent to the adjacent blade platforms and a sealing effect is achieved. In this way one becomes axial leakage current virtually completely prevented.
  • Another advantage lies in the ease of manufacture and Assembly of the sealing system. Because the sealing system on the peripheral surface is not necessarily fixed a rotor blade coupled. Assembly or repair work on a blade, e.g. exchanging a Blade, are thus possible without great effort. The Sealing system remains unaffected and can thus multiple times be used.
  • the sealing system has a circumferentially extending On sealing element.
  • the gap extends substantially in the radial and axial direction and in the circumferential direction of the rotor.
  • a along the circumferential direction of the Rotor extending sealing element in the space is suitable especially good, possible axial leakage flows of coolant and / or also on hot action fluid with high efficiency to hinder.
  • an upstream one axial leakage flow e.g. a hot gas from the Flow channel of a gas turbine, which extends along the peripheral surface spreads, by the sealing element effectively with special needs.
  • the leakage flow is in this case by the obstacle Delayed in the space and finally on the leakage flow facing side of the sealing element to a standstill come (simple throttle).
  • the opposite of the leakage flow Side of the sealing element and in the axial Direction adjoining part of the gap becomes by the simple sealing element against an impact with the leakage medium, e.g. hot action fluid or coolant, already effectively protected.
  • the sealing element is movable in the radial direction. Thereby it is achieved that the sealing element under centrifugal force in the radial direction from the axis of rotation of the rotor away. This property is purposefully exploited to a significantly improved sealing effect on the blade platform to achieve a blade.
  • the sealing element comes while under centrifugal force in Contact with the radially spaced from the peripheral surface, in Circumferentially adjacent blade platforms and is pressed firmly against the blade platforms.
  • the radial Mobility of the sealing element can by appropriate Dimensioning of the recess and the sealing element be ensured.
  • Another advantage is that thereby the sealing element for any maintenance purposes or at a Failure of the blade without additional tools and without the risk of caking of the sealing element due to a oxidizing or corrosive attack at high operating temperatures easy to remove and replace if necessary is.
  • the sealing element comprises a first partial sealing element and a second partial sealing element, wherein the first partial sealing element and the second partial sealing element intermesh.
  • the partial sealing elements can be designed so that they are in special way a partial sealing function for different Take over areas to be sealed in the intermediate space. Such different areas in the space be about suitable sealing surfaces on the groove bottom, at the Shovel platform of the first blade or at the paddling platform the second blade formed.
  • the partial sealing elements complement each other by their arrangement to a Pair of partial sealing elements to a sealing element, wherein the Sealing effect of the pair is greater than that of a partial sealing element.
  • the rotor has a running disk on which the peripheral surface and the receiving structure, wherein the peripheral surface of a first peripheral surface edge and one along the axis of rotation the first peripheral surface edge opposite having the second peripheral surface edge, and the receiving structure a first pulley groove and one in the circumferential direction the running disk to the first disk groove second objected Sliding groove has, and the blade root of the first Run shovel into the first rotor groove and the blade foot the second blade inserted into the second pulley groove is.
  • the attachment of the rotatable blades is so that in the operation of the turbomachine they can Shovel stresses due to flow and centrifugal forces as well pick up by blade vibrations with high security and the forces acting on the running disk and finally can transfer the entire rotor.
  • the attachment of the Blade can be done for example by axial grooves, each blade individually in a dedicated, extending substantially in the axial direction, Disk groove is clamped.
  • axial grooves for low loads, e.g. in axial compressor blades of compressors, are simple fastenings of the blade, for example with a swallowtail or lava foot, possible.
  • Plug foot and the axial Tannenbaumfuß for Steam turbine power amplifiers with long blades and accordingly large blade centrifugal forces comes in addition to the so-called Plug foot and the axial Tannenbaumfuß in question.
  • the axial Fir-tree fastening is also preferably used in thermally highly loaded blades in gas turbines.
  • the Peripheral surface a first peripheral surface edge and a second Peripheral surface edge as partial areas.
  • the first peripheral surface edge upstream and the second peripheral surface edge is located downstream.
  • the sealing system is on the first peripheral surface edge and / or arranged on the second peripheral surface edge.
  • the arrangement of the sealing system on the first, for example arranged upstream, peripheral surface edge primarily limits the entry of streaming hot Action fluid in the space, and thus prevents one Damage to the blade.
  • the arrangement of the sealing system on the second, downstream, circumferential surface edge serves primarily to prevent the escape of coolant, e.g. under a certain pressure standing cooling air in the space, in the axial direction along the peripheral surface over the second peripheral surface edge in the flow channel largely to prevent. Since the hot action fluid in the flow direction Relaxed, the pressure of the hot action fluid continuously degraded in the flow direction.
  • One under one certain pressurized coolant in the space is therefore towards the lower ambient pressure from the gap emerge, ie at the downstream peripheral surface edge.
  • a peripheral surface center region formed in the axial direction of the first Peripheral peripheral edge and the second peripheral edge of the surface bordered is, wherein the sealing system at least partially on the Circumferential center area is arranged.
  • the peripheral surface center area forms a portion of the peripheral surface.
  • the sealing system is arranged on different sub-areas. In the Arrangement of the sealing system are also combinations of different Subareas conceivable. The specified sealing system offers therefore with regard to the adaptation to concrete requirements with regard to the sealing effect to be achieved a very great flexibility.
  • a significant improvement of the simple ones described above Solution with a circumferentially extending sealing element results from the combination of the sealing element with one or more other sealing elements.
  • at least one other sealing element provided, which extends in the circumferential direction and axially spaced from the sealing element is arranged.
  • the gap In particular, before a possible entry of hot Action fluid from both the upstream region higher Pressure as well as from the downstream area lower Pressure of the flow channel very effectively protected. at the same time the sealed space becomes usable for a Coolant, e.g. Cooling air.
  • the coolant is thereby under Pressure supplied to the gap and, above all, for efficient Internal cooling of the thermally highly loaded rotor, the Blade platform and the radially adjacent to the blade platform Airfoil, used.
  • Another advantageous Use of the pressurized coolant in the Interspace consists in the utilization of its blocking effect opposite the hot action fluid in the flow channel.
  • the sealing elements By the structural design of the sealing elements and the choice the pressure of the coolant in the gap is reached that the pressure difference between the coolant and the hot action fluid sufficiently low but high enough is to be compared to the hot action fluid a barrier effect to achieve.
  • the ruling in the gap must Pressure of the coolant only slightly above the upstream Pressure of the hot action fluid lie. The bigger the Sealing effect of the sealing elements, the lower fall eventual residual leakage flows of coolant into the flow channel out.
  • the sealing element engages in a recess, in particular into a groove, in the circumferential area.
  • the Recess will also on the peripheral surface one Sealing surface prepared, which expediently as a partial surface the recess is formed.
  • this sealing surface for example, executed on the groove base.
  • the sealing element is the sealing surface with accordingly low and well-defined surface roughness.
  • the first partial sealing element and the second Part sealing element relative to each other in the circumferential direction movable will be a customized system of partial sealing elements provided.
  • the relative movement of the partial sealing elements in the circumferential direction allows an adapted mesh the partial sealing elements, depending on the thermal and / or mechanical loading of the rotor.
  • the adapted System of partial sealing elements can be carried out this way be that under the action of external forces, e.g. the centrifugal force and the normal and bearing forces, in a sense adjusted itself to develop its sealing effect.
  • possible thermally or mechanically induced Stresses due to the movable pair of partial sealing elements significantly better balanced.
  • the first Part sealing element and the second partial sealing element in each case one adjacent to the peripheral surface disc sealing edge and a Platform sealing edge adjacent to the blade platform.
  • the respective platform sealing edge can continue in essentiallyteildichtkanten be functionally subdivided.
  • a first formerlyteildichtkante and a second formerlyteildichtkante provided be, with the first platform part sealing edge to the Blade platform of the first blade and the second Deckteildichtkante to the blade platform of the second Blade adjoins.
  • first and the second partial sealing element With the paired arrangement of the first and the second partial sealing element to a sealing element is a particularly effective Gasket achieved.
  • first overlap and the second partial sealing element wherein the platform sealing edge and the disk sealing edge of the first partial sealing element to the platform sealing edge or disk sealing edge of the second Part sealing element adjacent.
  • This will pair in the Arrangement of the two partial sealing elements a good fit realized and thus by the sealing element a good seal against penetration of hot action fluid into the gap and / or leakage of coolant into the flow channel reached.
  • the sealing element is made of a highly heat-resistant material, in particular of a nickel-based or cobalt-based alloy, produced. These alloys still have sufficient elastic deformation properties.
  • the material of the sealing element to avoid of impurities or diffusion damage and for warranty a uniform thermal expansion of the rotor, in particular the blade platform of the blade, on the material of the rotor is selected adapted.
  • the sealing system has a Labyrinth sealing system, in particular a labyrinth gap sealing system on.
  • the operation of a labyrinth sealing system is based on a most effective throttling of the hot action fluid and / or the coolant in the sealing system and a thus caused extensive suppression of an axial directed leakage current (leakage mass flow) through the Gap.
  • a residual leakage current through existing sealing gaps, as in labyrinth gap seals occur in general, taking into account the so-called Bridging factor can be calculated.
  • labyrinth gap sealing systems which are also used as see-through seals be referred to, compared to so-called comb-groove sealing systems an up to 3.5 times larger leakage current through the sealing gap.
  • labyrinth gap sealing systems due to the remaining sealing gap against the Comb-groove sealing systems have the great advantage that they themselves for large thermally and / or mechanically induced relative elongations are suitable in the rotor.
  • the sealing system is in one piece, in particular by Material removal from the running disk, manufactured.
  • a Design of the sealing system e.g. as a labyrinth seal system this is by at least two in the circumferential direction of the rotor disk extending and axially spaced apart Realized sealing elements on the peripheral surface. These sealing elements can be made by turning the entire throttle plates be executed.
  • the one-piece production has the Advantage that you do not have an additional connecting element between the labyrinth seal system and the peripheral surface needed. Process technology can thus machining the disk and the production of the labyrinth seal system in one Step and be performed on a lathe which is very inexpensive.
  • the sealing element at its outer radial End a sealing tip, especially a knife edge on.
  • Residual leakage through the gap becomes critical influenced by the executable sealing gap width, i.e. for example, the distance between the outer radial End of the sealing element and the adjacent thereto to be sealed Blade platform.
  • the executable sealing gap width i.e. for example, the distance between the outer radial End of the sealing element and the adjacent thereto to be sealed Blade platform.
  • Low production is an increase in the outer radial End of the sealing element provided.
  • It can also be a Seal gap bridging be done by the sealing tip or the knife edge with a small oversize made the radial installation dimension of the blade platform becomes. By rubbing on the sealing tip or the knife edge to the bucket platform, the sealing gap when inserting the blade into the receiving structure, e.g. in a Axial groove of a running disk, bridged. This way will closed the sealing gap, achieved an improved seal and the axial leakage current is further reduced.
  • a gap sealing element for sealing a substantially axially extending Gaps provided, with the gap between the blade platform the first blade and the blade platform the second blade is formed and in fluid communication with the gap is.
  • the gap sealing element prevents that a leakage current through the gap occurs.
  • One Such leakage flow is directed substantially radially and can thereby both from the gap through the gap radially outward as well as through the gap in the gap radially be oriented inward.
  • the flow channel of the turbomachine for example a compressor or a gas turbine
  • the entry of the action fluid for example of the hot gas in a gas turbine
  • the gap sealing element prevents the escape of coolant, eg cooling air, from the gap through the gap radially outward into the flow channel.
  • a cavity can be connected to the gap radially outward, which is formed by the circumferentially adjacent first and second blades (so-called box design of a blade).
  • the gap sealing element prevents the possible entry of hot action fluid from the gap through the gap radially outward into the cavity.
  • the cavity sealed by the gap sealing element can be exposed to a coolant, for example cooling air. This is pressurized in the cavity and is available, for example, for efficient internal cooling of the thermally highly stressed blade or for other cooling purposes.
  • a further advantageous use of the pressurized coolant in the cavity is the utilization of its blocking action with respect to the hot action fluid in the flow channel.
  • the gap sealing element is through a gap sealing plate manufactured, which has a gap sealing edge, the under Centrifugal force engages the gap and the gap closes.
  • the embodiment of the gap sealing element as Gap sealing sheet is a simple and inexpensive solution.
  • a design as a thin metal strip, which has a longitudinal axis and a transverse axis possible.
  • the gap sealing edge extends in essentially centered on the metal strip along the longitudinal axis and can easily by folding over the metal strip be prepared.
  • the gap sealing element is Conveniently arranged in the intermediate space. In operation of the Turbomachine is then the gap sealing element as a result of Rotation determined by the radially outward centrifugal force pressed against the adjacent blade platform, wherein the gap sealing edge engages in the gap and this effectively seals.
  • the gap sealing element of a high heat resistant Material in particular of a nickel-based or cobalt-based alloy, produced. Own these alloys also sufficient elastic deformation properties.
  • the material of the gap sealing element is adapted to the material the rotor is selected, causing impurities or Diffusion damage can be avoided. Furthermore, a uniform thermal expansion or contraction of the rotor, in particular the blade platform of the blade, ensured.
  • the gap sealing element radially adjoins the Sealing system on.
  • a sealing system arranged on the peripheral surface especially with a labyrinth seal system, is one particular effective sealing of the gap to possible Leakage flows on hot action fluid and / or coolant reached.
  • this remains a centrifugal assisted Sealing effect of the gap sealing element for sealing an axially extending gap exist.
  • this Combination reduces the sealing system substantially axially directed leakage currents, while the gap sealing element the substantially radially directed leakage currents reduced.
  • This functional separation is also a Flexible structural adaptation to different rotor geometries readily possible.
  • the gap sealing element and the Sealing system complement each other very effectively.
  • a preferred embodiment is in the turbomachine with the extending along a rotation axis Rotor the receiving structure produced by a circumferential groove, wherein the peripheral surface is a first peripheral surface and a opposite along the axis of rotation of the first peripheral surface second peripheral surface having, respectively axially adjacent to the circumferential groove, wherein on the first and / or on the second peripheral surface in the gap the sealing system is provided.
  • the turbomachine is a gas turbine.
  • FIG. 1 shows a half section through a gas turbine 1.
  • the gas turbine 1 has a compressor 3 for combustion air, a combustion chamber 5 with burners 7 for a liquid or gaseous fuel and a turbine 9 for driving the compressor 3 and one not shown in Figure 1 Generator on.
  • the turbine 9 are fixed Vanes 11 and rotatable blades 13 on respective radially extending, not shown in half section, Wreaths along the axis of rotation 15 of the gas turbine. 1 arranged.
  • a successive along the axis of rotation 15 Pair of a wreath of vanes 11 (Vane ring) and a ring of running blades 13 (Running blade ring) referred to as turbine stage.
  • Each vane 11 has a paddle platform 17, which for Fixation of the relevant vane 11 on the inner turbine housing 19 is arranged.
  • the paddle platform 17 provides while a wall element in the turbine 9 is the blade platform 17 is a thermally heavily loaded component, which the outer boundary of the flow channel 21 in the turbine 9 forms.
  • the blade 13 is on the along the Rotation axis 15 of the gas turbine 1 arranged turbine rotor 23 attached via a corresponding blade platform 17.
  • the turbine runner 23 may be e.g. from several, in Figure 1, not shown, the blades 13 receiving Sliding wheels assembled by a not shown Tie rods held together and by Hirth gearing heat expansion tolerant centered on the axis of rotation 15 are.
  • the turbine runner 23 forms together with the Blades 13, the rotor 25 of the turbomachine 1, in particular the gas turbine 1.
  • Air L sucked from the environment.
  • the air L is in the compressor 3 compressed and thus simultaneously preheated.
  • the combustion chamber 5 is the air L with the liquid or gaseous Fuel brought together and burned.
  • a before the compressor 3 from suitable withdrawals 27 removed part the air L serves as cooling air K for cooling the turbine stages, whereby e.g. the first turbine stage with a turbine inlet temperature from about 750 ° C to 1200 ° C acted upon becomes.
  • a relaxation and cooling takes place the hot action fluid A, hereinafter referred to as hot gas A, which flows through the turbine stages and thereby set the rotor 25 in rotation.
  • FIG. 2 shows a detail in a perspective view a running disk 29 of a rotor 25.
  • the running disk 29 is centered along the axis of rotation 15 of the rotor 25.
  • the running disk 29 has a receiving structure 33 for attachment of blades 13 of the gas turbine 1 on.
  • the pickup structure 33 is through recesses 35, in particular by grooves, made in the runner 29.
  • the recess 35 is as axial pulley groove 37, in particular as axial Fir tree groove, executed.
  • the running disk 29 has a peripheral surface 31 on, at the outer radial end of the rotor disk 29 is arranged.
  • the peripheral surface 31 is through the outer radial boundary surface of the rotor 25, respectively the running disk 29, defined.
  • the thus defined peripheral surface 31 does not include the axial drive pulley groove 37 designed receiving structure 33.
  • a first peripheral surface edge 39A and a second peripheral surface edge 39B formed on the peripheral surface 31st.
  • the first peripheral surface edge lies 39A along the axis of rotation 15 the second Peripheral surface edge 39 B on the peripheral surface 31 opposite.
  • a peripheral surface center region 41 formed in the axial direction of the first peripheral surface edge 39A and the second peripheral surface edge 39B is bounded.
  • FIG. 1 A perspective view of a section of a running disk 29 with inserted blade 13A is shown in FIG shown.
  • the running disk 29 has over its full circumference, to its peripheral surface 31 toward open pulley grooves 37A, 37B, which are substantially parallel to the axis of rotation 15th of the rotor 25 run, but also obliquely thereto could be.
  • the pulley grooves 37A, 37B are with undercuts 59 equipped.
  • Of the Blade foot 43A rests with longitudinal ribs 61 on the undercuts 59 of the pulley groove 37A.
  • the blade 13A upon rotation of the rotor disk 29 to the axis of rotation 15 counter to in the direction of the longitudinal axis 47 of the blade 13A occurring centrifugal forces held securely.
  • Radially outward along the longitudinal axis 47 of the blade root 43A has the blade 13A widened trained area, the so-called paddle platform 17A.
  • the blade platform 17A has a disk-side base 63 and an outside of the disk-side base 63 65 on. On the outside 65 of the blade platform 17A, there is an airfoil 45 of the blade 13A. On the blade 45 flows to the operation of the rotor 25th required hot gas A over, generating a torque on the running disk 29.
  • a coolant K for example, cooling air K
  • an unillustrated supply line through the Running disk 29 in the blade root 43A of the blade 13A directed and from there to suitable, also in the figure 3, not shown, supply lines of the internal cooling system.
  • a Sealing system 51 is provided to premature leakage of the coolant K, in particular the cooling air K in the region of the blade root 43A and the blade platform 17 .
  • the sealing system 51 is on the peripheral surface 31 is disposed on the second peripheral surface edge 39B.
  • the sealing system 51 has a circumferential direction the running disk 29 extending sealing element 53.
  • One another sealing element 55 is provided and extends into Circumferential direction of the rotor 29 axially spaced from the Sealing element 53.
  • the sealing element 53 and the further sealing element 55 each engage in a recess 35, in particular in a groove, in the peripheral surface 31 a.
  • the sealing system 51 seals the gap 49, which between the Blade platform 17A of the blade 13A and a blade platform 17B of a second blade 13B, which is dashed shown and in a second pulley groove 37 B, in the circumferential direction of the rotor 29 to the first rotor groove 37A is spaced, and the peripheral surface 31 is formed.
  • FIG 4 shows a side view of a blade 13 with Sealing system 51.
  • the sealing system 51 is shown as a partial section in the Figure 4 illustrates.
  • the sealing system 51 is on the first Peripheral surface edge 39A and on the second peripheral surface edge 39B arranged in the intermediate space 49.
  • Related to the flow direction of the hot gas A is the first Peripheral surface edge 39A upstream on the peripheral surface 31st the running disk 29 and the second peripheral surface edge 39B downstream.
  • the arrangement of the sealing system 51 on the first, upstream, peripheral surface edge 39A bounded primarily the entry of flowing hot gas A in the intermediate space 49. This will damage the Blade 13 and the running disk 29 in the region of the peripheral surface 31 prevented.
  • the arrangement of the sealing system 51 on the second, downstream, circumferential surface edge 39B serves primarily to prevent the escape of a coolant K, e.g. under a certain pressure standing cooling air K in the intermediate space 49, in the axial direction along the peripheral surface 31 over the second peripheral surface edge 39B in the To prevent flow channel as efficiently as possible.
  • a coolant K e.g. under a certain pressure standing cooling air K in the intermediate space 49
  • the hot gas A relaxes in the flow direction.
  • the pressure of the hot gas A in the flow direction continuously degraded.
  • One under a certain Pressurized coolant K in the intermediate space 49 is therefore in Direction of lower ambient pressure from the gap 49 emerge, ie at the downstream arranged second peripheral surface edge 49B.
  • the sealing system 51 on the first peripheral surface edge 39A and on the second peripheral surface edge 39B seals the gap 49 in both directions. This embodiment therefore offers great security both against the entry of hot gas A in the gap 49th as well as to the exit of coolant K from the gap 49th
  • the sealing system 51 On the first peripheral surface edge 39A, the sealing system 51, a sealing element 53 which extends in the circumferential direction of the Running disk 29 extends on.
  • the sealing element 53 engages in a recess 35, in particular in a groove, which is incorporated in the peripheral surface 31.
  • the sealing system 51 has a sealing element 53, which extends in the circumferential direction.
  • One another sealing element 55 is on the second peripheral surface edge 39B provided.
  • the further sealing element 55 extends in the circumferential direction of the rotor disk 29 and is axially spaced arranged to the sealing element 53.
  • the embodiment of the sealing system 51 by one or more Sealing elements 53, 55 is particularly well suited to in the space 49 possible axial leakage flows of coolant K and / or hot gas A with increased efficiency hinder. So will the entry of an upstream axial leakage flow, e.g. the hot gas A from the flow channel a gas turbine 1, over the first peripheral surface edge 39A along the peripheral surface 31 in the intermediate space 49th flows through, arranged on the first peripheral surface edge 39 Sealing system 51 effectively hindered. at the same time is the occurrence of an axial leakage flow coming out of the Interspace 49 out along the second peripheral surface edge 39B is directed through the obstacle in the form of the sealing elements 53, 55 reliably prevented.
  • an upstream axial leakage flow e.g. the hot gas A from the flow channel a gas turbine 1
  • the first peripheral surface edge 39A along the peripheral surface 31 in the intermediate space 49th flows through, arranged on the first peripheral surface edge 39 Sealing system 51 effectively hindered.
  • the sealed gap 49 is thus well usable for a coolant K, e.g. Cooling air K.
  • a coolant K e.g. Cooling air K.
  • This can be under Be put pressure and then for efficient internal cooling the thermally highly loaded rotor 25, in particular the Paddle platform 17 and along the longitudinal axis 47 to the Paddle platform adjacent blade 45, used become.
  • Another advantageous use of under pressure standing coolant K in the intermediate space 49 is in the blocking action given to the hot gas A in the flow channel. By this blocking effect of the coolant K is the entrance of hot gas A in the intermediate space 49 largely prevented.
  • the sealing elements 53, 55 are each in the radial direction movably disposed in the recess 35 so that in operation of the rotor 25 due to the action of centrifugal force on the Sealing elements 53, 55 over a conventional embodiments improved sealing effect is achieved. Under effect the centrifugal force, the sealing elements 53, 55 are parallel move radially outward to the longitudinal axis 47. Here is the disk-side base 63 of the blade platform 17 opposite possible axial leakage flows out of the gap 49 out or sealed into the space 49 in very effective.
  • the radial mobility of the sealing elements 53, 55 can by appropriate design of the recess 35 and the sealing element 53, 55 are ensured. Thereby are the sealing elements 53, 55 and for any maintenance purposes or in case of failure of the blade 13 without additional Tools and without the risk of caking of the sealing element 53 due to an oxidizing or corrosive attack easily remove at high operating temperatures and replace if necessary.
  • the sealing element 53, 55 has a first Partial sealing element 67A and a second partial sealing element 67B on.
  • the first partial sealing element 67A and the second partial sealing element 67B interlock with each other.
  • the partial sealing elements 67A, 67B complement each other by their paired arrangement Sealing element 53, 55 in a special way, the scored Sealing effect of the paired partial sealing elements 67A, 67B larger is than that of a single partial sealing element 67A, 67B.
  • partial sealing elements 67A, 67B By a particularly advantageous embodiment of the partial sealing elements 67A, 67B to the respective areas to be sealed in the space 49 ensures that the achieved sealing effect the paired arrangement is larger than it is about one one-piece sealing element 53 would be feasible.
  • a possible, particularly advantageous embodiment of the partial sealing elements 67A, 67B will be described below with reference to FIGS. 5A to 5D and Figures 6A to 6D presented.
  • the sealing element 53, 55 shown in FIG. 4 is composed of two intermeshing partial sealing elements 67A, 67B in a preferred embodiment.
  • the first partial sealing element 67A is shown in different views: FIG. 5A shows a perspective view of the first partial sealing element 67A.
  • the first partial sealing element 67A has a disk sealing edge 69 and a platform sealing edge 71 opposite the disk sealing edge 69.
  • the disk sealing edge 69 adjoins the circumferential surface 31 and the platform sealing edge 71 abuts the disk-side base 63 of the blade platform 17.
  • FIG. 5B shows FIG 5C shows a view of the disk sealing edge 71 of the first partial sealing element 67A, FIG.
  • FIG. 5C shows a plan view of the first partial sealing element 67A
  • FIG. 5D shows a side view.
  • the platform sealing edge 71 has a first platform part sealing edge 71A and a second platform part sealing edge 71B. This subdivision of the platform sealing edge 71 into two platform part sealing edges 71A, 71B allows a simple design adaptation of the first partial sealing element 67A to the respective installation geometry of a moving blade 13 and a further moving blade 13B into a running disk 29 (see FIG. 3 and FIG.
  • FIGS. 6A to 6D are different views of the second partial sealing element 67B of one in FIG. 4 shown sealing element 53 shown.
  • Analogous to the first one Part sealing member 67A has the second partial sealing member 67B a disc sealing edge 69 and one of the disc sealing edge 69 opposite platform sealing edge 71 on. It is the platform sealing edge 71 continues in platform part sealing edges 71A, 71B functionally divided. It is a first deck section 71A and a second platform part sealing edge 71B provided.
  • Each of the partial sealing elements 67A, 67B is designed so that its respective center of mass adjacent to exactly one of the partial sealing element in question 67A, 67B associated with platform part sealing edges 71A, 71B is arranged. This is done by a stepped constructive Embodiment of each of the partial sealing elements 67A, 67B with a range of smaller material thickness and with one area greater material thickness achieved, with each area is associated with exactly one platform part sealing edge 71A, 71B.
  • the first partial sealing element 67A and the second partial sealing member 67B become one Sealing element 53 arranged in pairs. This will be a very efficient seal achieved.
  • the partial sealing elements 67A, 67B are designed so that they interlock in the installed state and overlap, with the platform sealing edge 71 and the disc sealing edge 69 of the first partial sealing element 67A to the platform sealing edge 71 and Scheibendichtkante 69th of the second partial sealing element 67B.
  • the partial sealing elements 67A, 67B are arranged so that areas with each different material thickness in contact with each other come.
  • the partial sealing elements 67A, 67B are, for example designed as metallic sealing plates. there a material is selected which is heat-resistant and sufficient having elastic deformation properties. When suitable material is, for example, a nickel base or Cobalt-based alloy in question. This ensures that that the material of the partial sealing elements 67A, 67B adapted to the material of the rotor 25 is selected. impurities or diffusion damage is thereby avoided and a uniform largely stress-free thermal expansion the rotor 25 is possible.
  • Figure 7 shows an axial plan view of a section of a Rotor 25 with a sealing element 53.
  • the rotor 25 has a running disk 29.
  • the running disk 29 has a first Sliding groove 37A and one in the circumferential direction of the rotor disk 29 second spaced apart from the first pulley groove 37A Wheel groove 37B.
  • the blade root 43A of the first blade 13A inserted in the pulley groove 37A and the blade root 43B of the second blade 13B into the second pulley groove 37B intervenes.
  • the blade platform 17A borders the first blade 13A to the blade platform 17B of second blade 13B on and between the blade platforms 17A, 17B and the peripheral surface 31 is a gap 49 formed.
  • a sealing element 53 is provided on the peripheral surface 31 is in the space 49.
  • the sealing element 53 has a disc sealing edge 69 and one of the disc sealing edge 69 opposite first platform part sealing edge 71A and a second platform part sealing edge 71B.
  • the sealing element 53 is in a recess 35, in particular in a groove in the Peripheral surface 31 used.
  • the edge of the window is adjacent 69 to the peripheral surface 31 at.
  • the first platform part sealing edge 71A is adjacent to the disk-side base 63 of the first one Vane platform 17A on, as well as the second platform part sealing edge 71B to the disk-side base 63 of the second Shovel platform 17B.
  • the sealing element 53 can thereby by two intermeshing, in the radial direction and in Circumferentially movable, paired partial sealing elements 67A, 67B, as in Figures 5A to 5D and in Figures 6A to 6D explained. This will be a special efficient sealing of the gap 49 allows. Especially be axially directed leakage currents from the gap 49 out or in the gap 49 into effective with special needs.
  • the sealing element 53 under centrifugal force is parallel to the longitudinal axis 47 radially outward from the axis of rotation 15th of the rotor 25.
  • This effect is exploited to a significantly improved sealing effect on each other adjacent blade platforms 17A, 17B of the adjacent To achieve blades 13A, 13B.
  • the sealing element 53 respectively each of the pairs not shown in FIG Partial sealing elements 67A, 67B (see Figures 5A-5D and 6A-6D), comes under centrifugal force in contact with the radially spaced from the peripheral surface 31, in the circumferential direction mutually adjacent blade platforms 17A, 17B and is pressed firmly against its disk-side base 63.
  • the sealing element 53 By appropriate dimensioning of the recess 35, in particular the groove, as well as the sealing element 53 is sufficient radial mobility ensured. In addition is a mobility of the sealing element 53 in the circumferential direction the running disk 29 is provided.
  • the sealing element 53 in particular each of the partial sealing elements not shown in FIG 67A, 67B (see Figures 5A-5D and Figures 6A-6D), will then be under the action of all external forces, such as for example, the centrifugal force, as well as the normal and / or bearing forces adjust yourself to develop its sealing effect.
  • the inclination of the platform part sealing edges 71A, 71B opposite the longitudinal axis 47 corresponds to the inclination of the disc-side base 63 of the blade platforms 17A, 17B.
  • a gap 73 may be formed. This gap 73 is in Fluid communication with the gap 49 and may optionally sealed by a simple gap sealing element (see Figure 11 and related description).
  • FIG. 1 An axial plan view of a section of a rotor 25 with an alternative embodiment to that of FIG Sealing element 53 is shown in FIG.
  • the scoop platform 17A of the first blade 13A is opposite to adjacent blade platform 17B of the second blade 13B offset in the radial direction.
  • Such a Offset ⁇ between circumferentially adjacent Bucket platforms 17A, 17B generally enter due to installation then, when the pulley grooves 37A, 37B opposite the axis of rotation 15 of the rotor 25 are inclined.
  • the sealing element 53 respectively, each of the not shown in the figure 7, paired with the sealing element 53 arranged partial sealing elements 67A, 67B (see Figures 5A-5D and Figures 6A-6D), is equipped with an offset sealing edge 75, which is the Offset ⁇ seals in a form-fitting manner.
  • the specified sealing concept is thus by appropriate design of the sealing element 53 flexible on different rotor geometries and Installation dimensions applicable.
  • Figure 9 shows a side view of a blade 13, the is inserted in a running disk 29, wherein in the intermediate space 49, the sealing system 51 on the peripheral surface center area 41 of the peripheral surface 31 is arranged.
  • the sealing system 51 is hereby used as a labyrinth sealing system 51A, in particular Labyrinth gap sealing system 51A, designed.
  • the labyrinth gap sealing system 51A is through several in the circumferential direction the running disk 29 extending and axially to each other spaced sealing elements 53 on the peripheral surface center region 41 realized.
  • the individual sealing elements 53 are in each case by aRocmmtes in the peripheral surface 41 Throttle plate 77A - 77E designed.
  • the mode of action of produced by the various throttle plates 77A-77E Labyrinth gap sealing system 51A is based on the most effective possible Throttling a flowing hot gas A and / or a Coolant K in the sealing system 51A and one caused thereby extensive reduction of an axially directed Leakage current through the gap 43.
  • the outer radial End 79 of a throttle plate 77A is from the disk side Base 63 of the blade platform 17 by a Seal gap 81 spaced. Through the sealing gap 81, as in the common in labyrinth gap seals 51A a residual leakage current in the intermediate space 49 occur.
  • the Labyrinth gap sealing system 51A has over other possible ones Labyrinthdichtsystemen the advantage that through the sealing gaps 81 a tolerance to thermally and / or mechanically induced Relative expansions in the rotor 25 is reached.
  • FIG. 1 An alternative embodiment of the one shown in FIG Sealing system 51 is shown in FIG.
  • the sealing system 51 is also designed as a labyrinth gap sealing system 51A, this being in one piece, in particular by material removal from the running disk 29, is made.
  • the labyrinth gap sealing system 51A is on the peripheral surface center area 41 of the running disk 29 is arranged.
  • the labyrinth gap sealing system 51A has a plurality of circumferentially of the running disk 29 extending and axially spaced apart On sealing elements 53.
  • the sealing elements 53 are through four throttle plates turned from the solid of the running disk 29 77A-77D.
  • thermally induced voltages between the running disk 29 and the labyrinth gap sealing system 51A No matter, since only one material is used.
  • Other Embodiments of the sealing element 53 as by a on the running disk welded throttle plate 77A are also possible.
  • the sealing element 53 has on the outer radial end 79 a sealing tip 83, in particular a knife edge on.
  • the sealing gap 81 can be increased by the addition the outer radial end 79 of the sealing element 53 on a as small as possible to be reduced. Residual leakage currents through the gap 49 are so further reduced.
  • a sealing gap bridging can be performed be by the sealing tip 83 or the knife edge with a small oversize compared to the radial installation dimension the blade platform 17 is produced.
  • the sealing gap 81 By a touch the sealing tip 83 or the knife edge to the disk side Base 63 of the paddle platform 17 is the sealing gap 81 when inserting the blade in the rotor disk 29 then bridged.
  • the sealing gap 81 becomes practical completely closed, a significantly improved sealing effect achieved and a possible axial leakage flow, about by the flowing hot gas A or by a coolant K, in Interspace 49 is further reduced.
  • FIG. 11 shows a perspective view of a detail a running disk 29 with inserted blade 13A, wherein the blade root 43A of the blade 13A into a first pulley groove 37A is used.
  • a second blade 13B which is shown in dashed lines, is with her blade foot 43B inserted into a second pulley groove 37B and in the circumferential direction the runner 29 adjacent to the blade 13A arranged.
  • On the peripheral surface 31 is on the peripheral surface center region 41 the sealing system 51, which as a labyrinth gap sealing system 51A is arranged.
  • the Sealing system 51A is characterized by several along the axis of rotation 15 spaced apart and in the circumferential direction of the rotor disk 29 extending sealing elements 53 made.
  • a gap sealing element 85 provided between the blade platform 17A of the blade 13A and the blade platform 17B of the second blade 13B a substantially axially extending gap 73 is formed, the in flow communication with the gap 49th stands.
  • the gap sealing element 85 is simpler Way through a suitable gap sealing plate, which a Gap sealing edge 87 has realized. The gap sealing edge engages under centrifugal force in the gap 73 and seals the gap 73.
  • the gap sealing element 85 is so in Intermediate space 49 arranged so that it radially to the sealing system 51, in particular to the labyrinth gap sealing system 51A, adjacent. By the gap sealing element 85 is largely prevented that a leakage current through the gap 73 occurs.
  • Such a leakage current through the gap 73 is substantially directed radially and can both from the gap 49 through the gap 73 radially outward, as well through the gap 73 in the intermediate space 49 radially inwardly be oriented.
  • a cavity 97 is formed. This one closes radially outward to the gap 73 (box design of the blade 13A, 13B). This prevents the gap sealing element 85 on the one hand the possible entry of hot gas A from the Interspace 49 through the gap 73 radially outward in the Cavity 97.
  • a coolant K e.g.
  • the coolant K is the cavity 97 is supplied under pressure and stands there for a efficient internal cooling of the thermally highly loaded rotor blades 13A, 13B or for other cooling purposes. Furthermore, the barrier effect of a pressurized Coolant K in the cavity 97 against the hot gas A in the flow channel be exploited.
  • Gap sealing element 85 made of a highly heat-resistant material, in particular from a nickel base or cobalt base alloy produced.
  • FIG. 12 shows a detail of a view in FIG. 11 shown arrangement along the section line XII-XII.
  • the Gap sealing element 85 is arranged in the intermediate space 49 and borders radially outward on the sealing element 53.
  • the gap seal member 85 In operation of the rotor 25 becomes the gap seal member 85 due to rotation by the radially outward along the longitudinal axis 47 directed Centrifugal force firmly against the disk-side base 63 of the adjacent platforms 17A, 17B, wherein the gap sealing edge 87 engages in the gap 73 and the Slit 73 thereby largely closes.
  • the gap sealing element 85 By the combination of the gap sealing element 85 with the sealing system 51 on the Peripheral surface 41, in particular with the labyrinth seal system 51A (see Figure 11) is a particularly effective seal the gap 49 against possible leakage flows of Hot gas A and / or achieved by coolant K.
  • the sealing system 51 substantially reduces the axially directed leakage currents, while the gap sealing element 85 substantially the radially directed leakage currents diminished (see Figure 11).
  • the gap sealing element 85 and the Sealing system 51 complement each other very effectively in this way.
  • FIG. 13 shows a perspective view of a rotor shaft 89 of a rotor 25, which extends along a rotation axis 15th extends.
  • a receiving structure 33 is axially by a plurality spaced circumferential grooves 91, which extend over the full circumference of the rotor shaft 89 extend, and in the peripheral surface 31 are incorporated, manufactured.
  • points the peripheral surface 31 a first peripheral surface 93 and a along the axis of rotation 15 of the first peripheral surface 93 opposite second peripheral surface 95.
  • the first peripheral surface 93 and the second peripheral surface 95 is adjacent axially against a circumferential groove 91.
  • the peripheral surfaces 93, 95 each form an outer radial boundary surface of the Rotor shaft 89.
  • FIG. 14 is a sectional view of a detail of FIG Rotor 25 with circumferential groove 91 and with inserted blade 13 is shown.
  • the circumferential groove 91 is made as Hammerkopfnut, which receives the blade root 43.
  • this form of blade attachment is preferred.
  • On the first peripheral surface 93 and on the second peripheral surface 95 is in each case a sealing element 53 in the intermediate space 49 intended.
  • the sealing element 53 extends in the circumferential direction the rotor shaft 89 and engages in a recess 35, in particular in a groove, in the rotor shaft 89 a.
  • the Sealing element 53 is arranged radially movable in the recess 35.
  • the sealing element 53 Upon rotation of the rotor shaft 89 about the axis of rotation 15, the sealing element 53 under centrifugal force along the longitudinal axis 47 of the blade 13 radially Move outward and firmly to the disk-side base 63 of the blade platform 17 is pressed. This will create the gap 49 sealed.
  • the sealing element 53 may be made two interlocking, not shown in FIG. 14, paired partial sealing elements 67A, 67B (see Figure 4 and Figures 5A-5D and 6A-6D).
  • FIG. 15 shows a sectional view of a section of a Rotor 25 with respect to Figure 14 alternative embodiment the blade attachment.
  • the circumferential groove 91 produced by a so-called technostannenbaumnut.
  • the blade root 43 of the blade 13 is accordingly produced as a fir tree root, which is in the circumferential groove 91, in particular in the designedstannenbaumnut engages.
  • this type of attachment of the blade 13 is at Rotation of the rotor 25 about the axis of rotation 15 a very effective power transmission to the rotor shaft 89 and a achieved a particularly secure hold.
  • Analogous to Figure 14 is in each case on the first peripheral surface 93 and on the second peripheral surface 95 in the intermediate space 49 a sealing element 53 for Seal the gap 49 is provided.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

L'invention concerne une turbomachine (1) comportant un rotor (25) s'étendant le long d'un axe de rotation (15). Ledit rotor (25) comprend une surface périphérique (31) définie par la surface de délimitation du rotor (25), ainsi qu'une structure de réception (33) et une première aube mobile (13A) et une seconde aube mobile (13B), qui présentent chacune une emplanture (43A,43B) et une plate-forme (17A,17B). La plate-forme (17A) de la première aube mobile (13A) et celle (17B) de la seconde aube mobile (13B) se jouxtent. Un espace intermédiaire (49) est formé entre les plates-formes (17A,17B) et la surface périphérique (31). Un système d'étanchéité (51) est prévu sur la surface périphérique (31), dans l'espace intermédiaire (49).

Claims (14)

  1. Turbomachine (1) comportant un rotor (25), qui s'étend le long d'un axe (15) de rotation et qui comprend une surface (31) périphérique définie par la surface radiale extérieure de délimitation du rotor (25), dans laquelle sont disposées plusieurs structures (33) de réception ainsi qu'une première aube (13A) mobile et une deuxième aube (13B) mobile, qui ont respectivement une emplanture (43A, 43B) d'aube et une plateforme (17A, 17B) d'aube voisine de l'emplanture (43A, 43B) d'aube, l'emplanture (43A) de la première aube (13A) mobile et l'emplanture (43B) de la deuxième aube (13B) mobile étant insérées dans la structure (33) de réception, de sorte que la plateforme (17A) de la première aube (13A) mobile et la plateforme (17B) de la deuxième aube (13B) mobile soient voisines et de manière à ménager entre les plateforme (17A, 17B) d'aube et la surface (31) périphérique, un espace (49) intermédiaire et il est prévu sur la surface (31) périphérique un système (51) d'étanchéité dans l'espace (49) intermédiaire, le système (51) d'étanchéité ayant un élément (53) d'étanchéité, qui s'étend dans la direction périphérique et qui comprend un premier sous-élément (67A) d'étanchéité et un deuxième sous-élément (67B) d'étanchéité,
       caractérisé en ce que
       le premier sous-élément (67A) d'étanchéité et le deuxième sous-élément (67B) d'étanchéité s'interpénètrent, et les sous-éléments (67A, 67B) d'étanchéité sont mobiles l'un par rapport à l'autre dans la direction périphérique.
  2. Turbomachine (1) suivant la revendication 1,
       caractérisé en ce que le rotor (25) a un disque (29) mobile, qui entoure la surface (31) périphérique et la structure (33) de réception, la surface (31) périphérique ayant un premier bord (39A) de surface périphérique et un deuxième bord (39B) de surface périphérique opposé le long de l'axe (15) de rotation au premier bord (39A) de surface périphérique, la structure (33) de réception ayant une première gorge (37A) de disque mobile et une deuxième gorge (37B) de disque mobile à distance, suivant la distance périphérique du premier disque (29) mobile, de la première gorge (37A) de disque mobile et l'emplanture (43A) de la première aube (13A) mobile étant insérée dans la première gorge (37A) de disque mobile et l'emplanture (43B) de la deuxième aube (13B) mobile dans la deuxième gorge (37B) de disque mobile.
  3. Turbomachine (1) suivant la revendication 2,
       caractérisé en ce que le système (51) d'étanchéité est disposé sur le premier bord (39A) de surface périphérique et/ou sur le deuxième bord (39B) de surface périphérique.
  4. Turbomachine (1 ) suivant la revendication 2 ou 3,
       caractérisé en ce qu'il est formé sur la surface (31) périphérique une zone (41) médiane de surface périphérique, qui est bordée dans la direction axiale par le premier bord (39A) de surface périphérique et par le deuxième bord (39B) de surface périphérique et en ce que le système (51) d'étanchéité est disposé au moins en partie sur la zone (41) médiane de surface périphérique.
  5. Turbomachine (1) suivant l'une des revendications précédentes,
       caractérisé en ce qu'il est prévu au moins un autre élément (55) d'étanchéité, qui s'étend dans la direction périphérique et qui est axialement à distance de l'élément (53) d'étanchéité.
  6. Turbomachine (1) suivant la revendication 5,
       caractérisé en ce que l'élément (53) d'étanchéité et/ou l'autre élément (55) d'étanchéité pénètrent dans un évidement (35), notamment dans une gorge, de la surface (51) périphérique.
  7. Turbomachine (1) suivant la revendication 5 ou 6,
       caractérisé en ce que l'élément (53) d'étanchéité et/ou l'autre élément (55) d'étanchéité est mobile dans la direction radiale.
  8. Turbomachine (1) suivant l'une des revendications 5 à 7,
       caractérisé en ce que l'élément (53, 55) d'étanchéité comprend un premier sous-élément (67A) d'étanchéité et un deuxième sous-élément (67B) d'étanchéité, le premier sous-élément (67A) d'étanchéité et le deuxième sous-élément (67B) d'étanchéité s'interpénétrant.
  9. Turbomachine (1) suivant la revendication 8,
       caractérisé en ce que le premier sous-élément (67A) d'étanchéité et le deuxième sous-élément (67B) d'étanchéité sont mobiles l'un par rapport à l'autre dans la direction périphérique.
  10. Turbomachine (1) suivant la revendication 8 ou 9,
       caractérisé en ce que le premier sous-élément (67A) d'étanchéité et le deuxième sous-élément (67B) d'étanchéité ont respectivement un bord (69) d'étanchéité de disque voisin de la surface (31) périphérique et un bord (41) d'étanchéité de plateforme voisin de la plateforme (17A, 17B) d'aube.
  11. Turbomachine (1) suivant la revendication 8, 9 ou 10,
       caractérisé en ce que le premier sous-élément (67A) d'étanchéité et le deuxième sous-élément (67B) d'étanchéité se recouvrent, le bord (71) d'étanchéité de plateforme et le bord (69) d'étanchéité de disque du premier sous-élément (67A) d'étanchéité étant voisin du bord (71) d'étanchéité de plateforme ou du bord (69) d'étanchéité de disque du deuxième sous-élément (67B) d'étanchéité.
  12. Turbomachine (1) suivant l'une des revendications 5 à 11,
       caractérisé en ce que l'élément (53, 55) d'étanchéité est en un matériau résistant bien à la chaleur, notamment en un alliage à base de nickel ou à base de cobalt.
  13. Turbomachine (1) suivant l'une des revendications précédentes,
       caractérisé par une réalisation en turbine (1) à gaz.
  14. Turbomachine (1) suivant la revendication 1 ou l'une des revendications 5 à 13,
       caractérisé en ce que la structure (63) de réception comprend une gorge (91) périphérique, en ce que la surface (31) périphérique comprend une première surface (93) périphérique et une deuxième surface (85) périphérique opposée le long de l'axe (15) de rotation à la première surface (93) périphérique, en ce que la première et la deuxième surfaces (93, 95) périphérique sont respectivement voisines axialement de la gorge (91) périphérique et en ce que le système (51) d'étanchéité est prévu dans l'espace (49) intermédiaire sur la première et/ou sur la deuxième surface (93, 95) périphérique.
EP00925282A 1999-05-14 2000-05-12 Turbomachine comportant un systeme d'etancheite pour un rotor Expired - Lifetime EP1180196B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP00925282A EP1180196B1 (fr) 1999-05-14 2000-05-12 Turbomachine comportant un systeme d'etancheite pour un rotor

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP99109630 1999-05-14
EP99109630 1999-05-14
PCT/EP2000/004317 WO2000070193A1 (fr) 1999-05-14 2000-05-12 Turbomachine comportant un systeme d'etancheite pour un rotor
EP00925282A EP1180196B1 (fr) 1999-05-14 2000-05-12 Turbomachine comportant un systeme d'etancheite pour un rotor

Publications (2)

Publication Number Publication Date
EP1180196A1 EP1180196A1 (fr) 2002-02-20
EP1180196B1 true EP1180196B1 (fr) 2005-02-16

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EP00925282A Expired - Lifetime EP1180196B1 (fr) 1999-05-14 2000-05-12 Turbomachine comportant un systeme d'etancheite pour un rotor

Country Status (8)

Country Link
US (1) US6565322B1 (fr)
EP (1) EP1180196B1 (fr)
JP (1) JP2002544432A (fr)
KR (1) KR20020005034A (fr)
CN (1) CN1252376C (fr)
CA (1) CA2372875A1 (fr)
DE (1) DE50009550D1 (fr)
WO (1) WO2000070193A1 (fr)

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JP2002544430A (ja) * 1999-05-14 2002-12-24 シーメンス アクチエンゲゼルシヤフト ロータに対する漏れ止め装置付き流体機械特にガスタービン
US7334331B2 (en) * 2003-12-18 2008-02-26 General Electric Company Methods and apparatus for machining components
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EP1180196A1 (fr) 2002-02-20
WO2000070193A1 (fr) 2000-11-23
KR20020005034A (ko) 2002-01-16
JP2002544432A (ja) 2002-12-24
CN1252376C (zh) 2006-04-19
CN1354820A (zh) 2002-06-19
DE50009550D1 (de) 2005-03-24
US6565322B1 (en) 2003-05-20
CA2372875A1 (fr) 2000-11-23

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