EP3421730B1 - Turbine für strömungsmaschine mit dichtring bestehend aus zwei teilen - Google Patents

Turbine für strömungsmaschine mit dichtring bestehend aus zwei teilen Download PDF

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Publication number
EP3421730B1
EP3421730B1 EP18179383.7A EP18179383A EP3421730B1 EP 3421730 B1 EP3421730 B1 EP 3421730B1 EP 18179383 A EP18179383 A EP 18179383A EP 3421730 B1 EP3421730 B1 EP 3421730B1
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EP
European Patent Office
Prior art keywords
turbine
radially
downstream
upstream
zone
Prior art date
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EP18179383.7A
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English (en)
French (fr)
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EP3421730A1 (de
Inventor
Olivier Arnaud Fabien Lambert
Franck Robert DROUET
Gaël Frédéric Claude Cyrille EVAIN
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3421730A1 publication Critical patent/EP3421730A1/de
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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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a turbine for a turbomachine, in particular for an aircraft turbojet or turboprop, as well as a method for mounting such a turbine.
  • a turbomachine in particular a double body turbomachine, conventionally comprises, from upstream to downstream, a blower, a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.
  • upstream and downstream are defined with respect to the direction of air circulation in the turbomachine.
  • internal and exitterior are defined radially with respect to the axis of the turbomachine.
  • a low pressure turbine engine turbine comprises a turbine shaft on which are mounted several successive stages each comprising an impeller and a distributor.
  • Each impeller comprises a disc carrying at its outer periphery substantially radial vanes, the discs of the different wheels being connected coaxially to each other and to the drive shaft of the turbine rotor by suitable means.
  • Each distributor comprises an internal annular platform and an external annular platform between which extend substantially radial blades.
  • the external platform of the distributor comprises means for hooking and fixing to an external casing of the turbine.
  • the set of distributors forms the fixed part of the motor called the stator.
  • each rotor wheel conventionally have wipers at their radially outer periphery, cooperating with a ring of abradable material so as to form sealing means of the labyrinth seal type.
  • Such a structure is for example known from the document FR 2 879 649 .
  • the document US2008 / 0175706 discloses another example of sealing means of labyrinth seal type assembled axially.
  • the object of the invention is in particular to provide a simple, effective and economical solution to this problem.
  • the present invention relates to a turbine for a turbomachine, for example for an airplane turbojet or turboprop, comprising a stator, a rotor comprising a rotor wheel comprising vanes whose radially outer periphery comprises at least one wiper s 'extending radially outwards, sealing means extending radially around the blades and comprising a sealing ring, the radially external end of the wiper cooperating with said sealing ring so as to form a seal labyrinth type, characterized in that said sealing ring comprises at least a first part, and a second part, axially offset from one another, the first part and the second part defining a groove in which is inserted the wiper), the first part and / or the second part each cooperating with at least one wiper of the blades located axially in r with regard to said first and second parts, the first part comprising a first projecting zone engaged by complementary shape in the axial direction in a first zone in the hollow of the second
  • the assembly previously mentioned between the first and the second part is thus of the tenon-mortise type.
  • the means for holding in position may comprise a radial support stop for the first part and a means for clamping the second part against the stator, the first part being arranged upstream of the second part.
  • the first part may include a recess opening radially outward and axially downstream, the second part comprising a recess opening radially outward and axially upstream, opposite the recess of the first part.
  • the recesses of the first and second parts then form the groove.
  • only one of the first and second parts can have a recess, the groove being delimited by said recess and by a radial surface of the opposite part.
  • the first part can be held radially, upstream, by the stator, the first part being held radially, downstream, by the second part.
  • the first part and the second part may comprise a block of abradable material mounted on a support, the first projecting and recessed areas of said first and second parts being formed on the supports.
  • the first part and the second part may be annular and may be formed of a succession of ring sectors, each ring sector having slots at its circumferential ends, sealing tongues being mounted in said slots between said sectors.
  • the first protruding area and the first recessed area may extend circumferentially over an angular range less than or substantially equal to the circumferential extension of a sector of the sealing ring.
  • the first projecting zone and the first hollow zone form a baffle limiting the rate of leakage of the gases circulating in the vein radially outward, between the first and second parts.
  • the aforementioned circumferential extension makes it possible to limit this leakage rate as much as possible.
  • the first part may comprise a second projecting zone engaged by complementary shape in a second hollow zone of the second part, or respectively of the first part, the first projecting and hollow zones being offset. radially with respect to the radially internal surface of the second protruding and recessed areas.
  • first protruding and recessed areas can be offset radially outward relative to the second protruding and recessed areas.
  • the first projecting area or the first recessed area can be offset axially with respect to the second projecting area or the second recessed area.
  • the baffle is enlarged in the axial direction, which contributes to maximizing the efficiency of the baffle by effectively limiting the gas leakage rate between the first part and the second part of the sealing ring. .
  • the stator may comprise a turbine casing comprising an annular wall, for example frustoconical, at least one flange extending radially inwards from the annular wall of the turbine casing, said flange bearing axially, upstream, on a radially external annular rim of the first part, said flange bearing axially, downstream, on a radially external annular rim of the second part.
  • a turbine casing comprising an annular wall, for example frustoconical, at least one flange extending radially inwards from the annular wall of the turbine casing, said flange bearing axially, upstream, on a radially external annular rim of the first part, said flange bearing axially, downstream, on a radially external annular rim of the second part.
  • Said flanges can be formed in the supports of the first and second parts.
  • the stator may include a downstream distributor, the downstream end of the second part being engaged in a groove in the downstream distributor.
  • the turbine housing flange can also be engaged in the groove of the downstream distributor
  • Each projecting zone can be attached to the first part or to the second part, at its base, and can have a free end opposite the base.
  • the first protruding area can belong to the first part, or respectively to the second part
  • the second protruding area can belong to the second part, or respectively to the first part.
  • the free end of the first projecting area can be offset axially with respect to the base of the second projecting area.
  • the free end of the second projecting zone can be offset axially with respect to the base of the first projecting zone.
  • the base of the first protruding area may be located axially opposite the base of the second protruding area.
  • the block of abradable material of the first part may have a downstream radial surface.
  • the block of abradable material of the second part may include a radial upstream surface.
  • the blocks of abradable material of the first and second parts can be in contact with each other at the level of said radial upstream and upstream surfaces.
  • the base of the second projecting zone can be offset axially, for example downstream, relative to the downstream surface of the block of the first part and / or relative to the upstream surface of the block of the second part.
  • the first part and / or the second part have a radially external surface intended to support the housing flange.
  • Said external bearing surface comprises at least one annular groove.
  • the part may include a fixing member, for example of U-shaped section, engaged by complementary shape on the stator.
  • the fixing member can be fixed to the support of the first part.
  • Each blade of the rotor wheel can comprise at least a first wiper and a second wiper, the first wiper extending radially outwards, beyond the second wiper.
  • the first wiper can be engaged in the groove defined by the first and second parts.
  • the second wipers can cooperate with radially internal and cylindrical or frustoconical surfaces of the first and second parts.
  • a low-pressure turbine 1 of a turbomachine is illustrated in the figure 1 .
  • the turbine 1 comprises a fixed casing 2, having a frustoconical wall 3 whose axis corresponds to the axis of the turbomachine and from which flanges 4, 5 extend radially inward.
  • the casing 2 comprises in particular an upstream flange 4 and a downstream flange 5.
  • upstream and downstream are defined by reference to the direction F of flow of the gas flow within the turbine 1, that is to say of left to right on the figure 1 .
  • Each flange 4, 5 comprises a first annular part 6 extending radially inwards from the frustoconical wall 3, and a second cylindrical part 7 extending downstream.
  • the upstream flange 4 further comprises an annular radial flange 8 extending radially inwards from the downstream end of the second part 7.
  • the stator of the turbine 1 notably comprises two distributor stages, which will be designated respectively upstream distributor 9 and downstream distributor 10, each distributor 9, 10 comprising a radially internal platform (not visible), a radially external platform 11a , 11b and fixed blades 12a, 12b connecting said platforms.
  • the external platform 11a of the upstream distributor 9 has a generally frustoconical wall 13, the downstream end of which comprises a support zone 14 comprising a first part 15 extending radially outwards and a second part 16 extending axially downstream.
  • the downstream end of the second part 16 of the support zone 14 is axially supported on the flange 8 of the upstream flange 4 of the casing 2, the second part 16 of the support zone 14 also being axially supported on the second part 7 of the upstream flange 4.
  • the upstream end of the external platform 11 of the downstream distributor 10 has a radially internal rim 17 and a radially external rim 18 extending axially upstream, radially spaced from one another.
  • the radially outer rim 18 bears radially on the radially outer surface of the second part 7 of the downstream flange 5.
  • the function of the radially inner rim 17 will be better described below.
  • the turbine 1 further comprises a sealing ring 19, fixedly mounted on the casing 2 and formed in two parts 20, 36, namely an upstream part 20 and a downstream part 36.
  • the sealing ring 19 is formed of several contiguous angular sectors 21 over the entire circumference, also visible at figures 2 to 4 .
  • the upstream part 20 comprises in particular an upstream block 22 of abradable material, of annular shape.
  • the upstream block 22 has a recess 23A at its downstream end, said recess 23A opening radially inward and axially downstream.
  • the external surface of the upstream block 22 is fixed to an upstream support 24, of annular shape.
  • the upstream support and the upstream block are thus segmented.
  • the upstream support 24 has a flange 25 located in a central region of the support 24 and extending radially outwards. The flange is capable of coming to bear axially on the downstream flange of the casing.
  • the radially external surface of the upstream support 24 further comprises an annular groove 26 located directly downstream of the rim 25.
  • the downstream end of the upstream support 24 forms an annular bearing area 27 of limited surface, capable of coming to bear radially on the downstream flange 5 of the casing 2.
  • the upstream support 24 comprises a recessed area 28 on its radially inner part, said recessed area 28 opening radially inward and axially downstream.
  • the upstream support 24 further comprises a projecting zone 29 extending axially downstream and extending circumferentially over almost the entire sector 21 concerned.
  • the protruding area 29 has a base 30 located upstream and a free end 31 opposite the base, located downstream.
  • the protruding area 29 is offset radially outward from the recessed area 28. Furthermore, the base 30 of the protruding area 29 is offset axially downstream from the upstream end 32 of the recessed area 28.
  • An annular fixing member 33 with a U-section is fixed at the upstream end of the upstream support 24, radially inside said upstream support 24.
  • Said upstream fixing member 33 comprises a radially external branch 34, suitable for coming radially supported on the external surface of the second part 7 of the upstream flange 4, and a radially internal branch 35 capable of coming to bear radially on the second part 16 of the support zone 15 and on the edge of the upstream flange 4.
  • a radial mounting clearance can be provided.
  • the upstream distributor 9 is thus fixed on the upstream flange 4 using the upstream fixing member 33.
  • This member 33 also makes it possible to fix the upstream support 24 on the upstream flange 4.
  • the downstream part 36 comprises in particular a downstream block 37 of abradable material, of annular shape.
  • the downstream block 37 has a recess 23B at its upstream end, said recess 23B opening radially inward and axially upstream.
  • the recesses 23A, 23B of the upstream 22 and downstream blocks 37 delimit a groove 39.
  • downstream block 37 The external surface of the downstream block 37 is fixed to a downstream support 38, of annular shape.
  • the downstream support 38 and the downstream block 37 are thus sectorized.
  • the downstream support 38 has a flange 40 located in a downstream area of the support 38 and extending radially outward.
  • the rim 40 is capable of coming into axial abutment on the downstream flange 5 of the casing 2.
  • the radially external surface of the downstream support 38 further comprises an annular groove 41 located upstream from the rim 40.
  • the upstream area of the downstream support 38 forms two annular support zones 42 of limited surfaces, located axially on either side of the groove 41. Said bearing zones 42 are capable of coming to bear radially on the flange 5 downstream of the casing 2.
  • the downstream support 38 comprises a projecting area 43 on its radially inner part, said projecting area 43 extending axially upstream and being engaged by complementary shape in the hollow area 28 of the upstream support 24.
  • the downstream support 38 further comprises a recessed area 44 extending circumferentially over almost the entire sector 21 concerned.
  • the projecting area 29 of the upstream support 24 is engaged by complementary shape in the hollow area 44 of the downstream support 38.
  • the protruding area 43 of the downstream support 38 includes a base 45 located downstream and a free end 46 opposite the base 45, located upstream.
  • the protruding area 43 is offset radially inward relative to the recessed area 44. Furthermore, the base 45 of the protruding area 43 is offset axially upstream relative to the downstream end of the recessed area 47.
  • downstream support 38 comes to bear radially on the radially external surface 48 of the internal rim 17 of the external platform 11b of the downstream distributor 10.
  • the downstream block 37 is in axial support on the radial surface upstream of the internal rim 17 of the external platform 11b of the downstream distributor 10.
  • the turbine 1 further comprises a rotor wheel 51 comprising blades 52, the radially outer periphery 53 of each blade 52 comprising a first wiper 54, axially central, and two second wipers 55 offset axially on either side of the first wiper 54.
  • the first and second wipers 54, 55 extend radially outwards, the first wiper 54 extending radially outward relative to the second wipers 55.
  • the first wiper 54 is engaged in the recess 23A, 23B of the upstream and downstream parts 20, 36 of the ring 19.
  • the second wipers 55 extend opposite the radially internal surfaces of the upstream and downstream blocks 22, 37.
  • the cumulative axial dimension of the recesses 23A, 23B that is to say the axial dimension of the groove 39, allows a displacement or an uncertainty of axial positioning of the rotor wheel 51, and therefore of the first wiper 54, by relative to the casing 2, such uncertainty may be due to manufacturing and mounting tolerances as well as mechanical and / or thermal stresses in operation.
  • the upstream distributor 9 is mounted inside the casing 2 ( figure 5 ), then the upstream part 20 of the ring 19 is engaged axially from downstream to upstream in the casing 2 ( figure 6 ), on the upstream flange 4 of the casing 2.
  • the upstream fixing member 33 is engaged on the upstream flange 4 and on the part 16 of the upstream distributor 9 so as to secure the upstream distributor 9 on the upstream flange 4.
  • the rotor wheel 51 comprising the blades 52 is then axially engaged in the casing 2, from downstream to upstream ( figure 7 ), the first wiper 54 being located, at least partially, in the recess 23A of the upstream abradable block 22.
  • downstream part 36 of the ring 19 is then axially engaged in the casing 2, from downstream to the upstream, so that the projecting 29 and hollow 28 areas of the upstream part can engage by shape cooperation in the hollow 44 and projecting 43 areas of the downstream part 36 ( figure 8 ).
  • the downstream part 36 is thus fixed on the upstream part 20.
  • the downstream distributor 10 is then engaged axially in the casing 2, from downstream to upstream (FIG. 10).
  • the rim 17 of the external platform 11 of the downstream distributor 10 comes into radial support with the downstream flange 5.
  • the internal rim 17 of the external platform 11b of the downstream distributor 10 comes into radial support on the radially internal surface of the support downstream 38 and bears axially on the downstream block 37, as indicated above.
  • the downstream support 38 is thus kept in abutment with the downstream flange 6 of the casing 2, using the downstream distributor 10.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Turbine (1) für Turbomaschinen bzw. Turbotriebwerke, enthaltend einen Stator (2, 9, 10) und einen Rotor, der ein Rotorrad (51) mit Schaufeln (52) aufweist, deren radial äußerer Umfang zumindest eine sich radial nach außen erstreckende Zunge (54) aufweist, Dichtungsmittel, die sich radial um die Schaufeln (52) herum erstrecken und einen Dichtungsring (19) aufweisen, wobei das radial äußere Ende der Zunge (54) mit dem Dichtungsring (19) so zusammenwirkt, dass eine labyrinthartige Dichtung entsteht,
    dadurch gekennzeichnet, dass
    der Dichtungsring (19) zumindest einen ersten Abschnitt (20) und einen zweiten Abschnitt (36) aufweist, die axial gegeneinander versetzt sind, wobei der erste Abschnitt (20) und der zweite Abschnitt (36) eine Nut (39) begrenzen, in welche die Zunge (54) eingefügt ist, wobei der erste Abschnitt (20) und/oder der zweite Abschnitt (36) jeweils mit zumindest einer Zunge (54, 55) der Schaufeln (52) zusammenwirken, die dem ersten und dem zweiten Abschnitt (20, 36) axial gegenüberliegen, wobei der erste Abschnitt (20) einen ersten vorspringenden Bereich (29) aufweist, der in axialer Richtung formschlüssig in einen ersten ausgesparten Bereich (44) des zweiten Abschnitts (36) eingreift, wobei der Stator (2, 9, 10) Mittel zum Halten des ersten und des zweiten Abschnitts (20, 36) in Stellung in Bezug auf den Stator (2, 9, 10) aufweist.
  2. Turbine (1) nach Anspruch 1,
    dadurch gekennzeichnet, dass
    die Mittel zum Halten in Stellung einen radialen Widerlageranschlag (4, 7) für den ersten Abschnitt (20) und ein Mittel zum Verspannen des zweiten Abschnitts (36) gegen den Stator (2, 9, 10) enthalten, wobei der erste Abschnitt (20) dem zweiten Abschnitt (36) vorgelagert ist.
  3. Turbine (1) nach Anspruch 1 oder 2,
    dadurch gekennzeichnet, dass
    der erste Abschnitt (20) radial stromaufwärts vom Stator (2, 9, 10) gehalten wird, während der erste Abschnitt (20) radial stromabwärts vom zweiten Abschnitt (36) gehalten wird.
  4. Turbine (1) nach einem der Ansprüche 1 bis 3,
    dadurch gekennzeichnet, dass
    der erste Abschnitt (20) und der zweite Abschnitt (36) ringförmig ausgebildet sind und aus einer Abfolge von Ringsektoren (21) bestehen, wobei jeder Ringsektor (21) im Bereich seiner Umfangsenden Schlitze aufweist, wobei Dichtungszungen in den Schlitzen zwischen den Sektoren (21) angeordnet sind.
  5. Turbine (1) nach einem der Ansprüche 1 bis 4,
    dadurch gekennzeichnet, dass
    der erste vorspringende Bereich (29) und der erste ausgesparte Bereich (44) sich umfänglich über einen Winkelbereich erstrecken, der kleiner oder im Wesentlichen gleich der Umfangserstreckung eines Sektors des Dichtungsrings (19) ist.
  6. Turbine (1) nach einem der Ansprüche 1 bis 4,
    dadurch gekennzeichnet, dass
    der erste Abschnitt (20) bzw. der zweite Abschnitt (36) einen zweiten vorspringenden Bereich (45) aufweist, der formschlüssig in einen zweiten ausgesparten Bereich (28) des zweiten Abschnitts (36) bzw. des ersten Abschnitts (20) eingreift, wobei die radial innere Fläche des ersten vorspringenden (29) und ausgesparten Bereichs (44) radial bezüglich der radial inneren Fläche des zweiten vorspringenden (45) und ausgesparten Bereichs (28) versetzt sind.
  7. Turbine (1) nach Anspruch 6,
    dadurch gekennzeichnet, dass
    der erste vorspringende Bereich (29) bzw. der erste ausgesparte Bereich (44) axial bezüglich des zweiten vorspringenden Bereichs (45) bzw. des zweiten ausgesparten Bereichs (28) versetzt ist.
  8. Turbine (1) nach einem der Ansprüche 1 bis 7,
    dadurch gekennzeichnet, dass
    der Stator ein Turbinengehäuse (2) enthält, das eine beispielsweise kegelstumpfförmige Ringwand (3) aufweist, wobei sich zumindest ein Flansch (5) von der Ringwand des Turbinengehäuses (2) der Turbine (1) radial nach innen erstreckt, wobei der Flansch (5) sich axial stromaufwärts an eine radial äußere Ringkante (25) des ersten Abschnitts (20) abstützt und der Flansch (5) sich axial stromabwärts an einer radial äußeren Ringkante (40) des zweiten Abschnitts (36) abstützt.
  9. Turbine (1) nach einem der Ansprüche 1 bis 8,
    dadurch gekennzeichnet, dass
    der Stator einen stromabwärtigen Leitapparat (10) enthält, wobei das stromabwärtige Ende des zweiten Abschnitts (36) in eine Nut des stromabwärtigen Leitapparats (10) eingreift.
  10. Verfahren zum Montieren einer Turbine (1) nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass es die folgenden Schritte umfasst:
    (a) Anbringen des ersten Abschnitts (20) an ein Gehäuse (2) der Turbine (1), indem der erste Abschnitt (20) axial von stromabwärts nach stromaufwärts in Bezug auf das Gehäuse (2) in Eingriff gebracht wird,
    (b) Montieren des Rotorrads (51) in das Gehäuse (2),
    (c) Montieren des zweiten Abschnitts (36) an den ersten Abschnitt (20), indem der zweite Abschnitt (36) axial von stromabwärts nach stromaufwärts in Bezug auf den ersten Abschnitt (20) in Eingriff gebracht wird,
    (d) wobei die Zunge (54) in Schritt (b) und/oder in Schritt (c) in die Nut (38) eingefügt wird.
EP18179383.7A 2017-06-26 2018-06-22 Turbine für strömungsmaschine mit dichtring bestehend aus zwei teilen Active EP3421730B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1755821A FR3068070B1 (fr) 2017-06-26 2017-06-26 Turbine pour turbomachine

Publications (2)

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EP3421730A1 EP3421730A1 (de) 2019-01-02
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US10934877B2 (en) * 2018-10-31 2021-03-02 Raytheon Technologies Corporation CMC laminate pocket BOAS with axial attachment scheme
DE102019216646A1 (de) * 2019-10-29 2021-04-29 MTU Aero Engines AG Laufschaufelanordnung für eine strömungsmaschine
FR3128970A1 (fr) 2021-11-05 2023-05-12 Safran Aircraft Engines Dispositif d’etancheite a labyrinthe pour une turbomachine d’aeronef

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Publication number Publication date
FR3068070A1 (fr) 2018-12-28
US10760441B2 (en) 2020-09-01
FR3068070B1 (fr) 2019-07-19
EP3421730A1 (de) 2019-01-02
US20190010818A1 (en) 2019-01-10

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