EP2787180A1 - Agencement d'aubes directrices pour une turbomachine - Google Patents

Agencement d'aubes directrices pour une turbomachine Download PDF

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Publication number
EP2787180A1
EP2787180A1 EP13162302.7A EP13162302A EP2787180A1 EP 2787180 A1 EP2787180 A1 EP 2787180A1 EP 13162302 A EP13162302 A EP 13162302A EP 2787180 A1 EP2787180 A1 EP 2787180A1
Authority
EP
European Patent Office
Prior art keywords
seal carrier
end portion
vane assembly
wedge
connection
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP13162302.7A
Other languages
German (de)
English (en)
Inventor
Hermann Klingels
Johann Geppert
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13162302.7A priority Critical patent/EP2787180A1/fr
Publication of EP2787180A1 publication Critical patent/EP2787180A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a stator blade assembly for a turbomachine according to the preamble of claim 1 and a turbomachine, in particular a gas turbine, with such a guide vane assembly.
  • turbomachines have an axially flow-through housing with a stator, which has a plurality of vanes.
  • the vanes have at their radially inner end an end portion which is releasably connected to a seal carrier.
  • the seal carrier serves to seal a gap between the vane, in particular the end portion, and a rotor of the turbomachine.
  • a disadvantage of the aforementioned form-fitting connection is that, for assembly reasons and due to tolerances, the projection and the receptacle are designed in such a way that a gap forms between them when the projection engages in the receptacle. Through the gap, an undesirable leakage flow can take place, which has a disadvantageous effect on the efficiency and / or the surge limit of the turbomachine.
  • An object of the invention is to provide an improved vane arrangement.
  • a vane arrangement which has a radially inner end section and a seal carrier.
  • the seal carrier is releasably connected to the end portion, wherein the connection between the seal carrier and the end portion has at least one spline connection.
  • An advantage of providing a splined connection for connecting the seal carrier to the end section may be, in particular, that there is no gap in the latter, as in the case of the connection known from the prior art, or that the latter is smaller. Therefore, in an advantageous embodiment, no leakage flows occur or are reduced, which in particular can have a positive effect on the efficiency and / or the surge limit of the turbomachine.
  • the end portion or the seal carrier may have a wedge-shaped projection.
  • the wedge-shaped projection can engage in a wedge-shaped receptacle of the other of the seal carrier and the end portion for producing a splined connection.
  • a splined connection is realized in a simple manner.
  • At least one clamping means may be provided, which serves for, in particular axial, clamping of the splined connection, wherein a tensioning means may in particular be a spring.
  • Clamping means can be arranged adjacent to each other in the circumferential direction.
  • the respective clamping means can be supported on one side against the seal carrier and on another side against the end section and / or a component which is in operative connection with the end section, in particular a bushing for supporting a guide blade root.
  • the clamping means may be designed such that it is supported on one side of at least two bushings, in a further development at least two, in particular at least three bushings in the circumferential direction overlaps.
  • the tensioning means preferably exerts such a force, in particular in the axial direction of the turbomachine, on the seal carrier that the wedge-shaped projection is tensioned into the wedge-shaped receptacle and thus a gap between the projection and the receptacle is reduced.
  • leakage currents can be further reduced.
  • a radially inner or radially outer, in particular cylindrical, contact surface of the projection and / or the receptacle can be formed, at least substantially, parallel to the axis of the turbomachine.
  • sealing means such as sealing honeycomb or a brush seal, can be reduced or avoided.
  • the contact surface of the projection and / or the receptacle may be flat.
  • a planar contact surface means in the sense of the invention in particular that the surface is not curved.
  • a Leitradschaufelfuß with the end portion movable or fixed, in particular integrally formed in the context of the invention, the term stator blade root is understood to mean, in particular, the radially inner end of a stator blade of the stator, which can be connected to the end portion.
  • the vane root may be a pin projecting from an airfoil of the vane.
  • the end portion In a movable connection between the Leitradschaufelfuß with the end portion, the end portion may be formed as an inner ring.
  • a fixed, in particular rotationally fixed, connection between the Leitradschaufelfuß with the end portion the end portion may be formed as an inner shroud.
  • an adjustment of the vane about its longitudinal axis is possible. In a fixed connection, the vane is not adjustable about its longitudinal axis.
  • the inner ring or the inner cover strip can be formed in one piece.
  • the inner ring and the inner cover strip may have a plurality of circumferentially adjacent segments.
  • An inner ring or inner cover band segment may be connected to a stator blade root or a plurality of stator blade roots.
  • a spline connection between the seal carrier and the end portion may be located upstream of the nozzle root and / or downstream of the nozzle root. Additionally or alternatively, a, in particular hook-like, positive connection for connecting the end portion may be provided with the seal carrier.
  • the seal carrier may be trough-shaped.
  • the seal carrier may have a bottom and at least two, in particular from the bottom, radially extending flanks.
  • the connection of the seal carrier with the end portion can take place via the flanks of the seal carrier.
  • the wedge-shaped projection or the wedge-shaped receptacle can be provided on at least one flank of the seal carrier.
  • the wedge-shaped portion or the wedge-shaped receptacle may be provided in an end portion of the flank remote from the ground.
  • a sealant carried by the seal carrier may protrude from the bottom of the seal carrier in a direction away from the end portion.
  • the vane arrangement described above can with particular advantage in a gas turbine, in particular an aircraft engine, with at least one compressor and / or Turbine stage can be used.
  • the use of the vane arrangement is not limited to the gas turbine and the aircraft engine, but can also be used in other turbomachinery.
  • guide vane assembly of a gas turbine has a plurality of vanes 1, wherein in FIG. 1 only a single vane 1 is shown.
  • the vane 1 has an airfoil 10 which is rotatably mounted at the radially inner end via a pin 11 in a bushing 40.
  • the rotatable mounting of the vane 1 allows adjustment about the longitudinal axis.
  • the not shown radially outer end of the vane 1 is coupled to an outer bearing ring.
  • the illustrated radially inner end of the vane 1 is coupled to an end portion in the form of an inner ring 2.
  • the guide vane 1 relative to the axial direction of the turbomachine (left-right in Fig. 1 ) is arranged between two blades, not shown.
  • the inner ring 2 has a plurality of circumferentially adjacent to each other inner ring segments 20, wherein in FIG. 1 a single inner ring segment 20 is shown.
  • the inner ring segment 20 is coupled to the guide vane 1 and surrounds the sleeve 40 and pin 11 in the radial direction. Furthermore, the inner ring segment 20 is connected to a seal carrier segment 30 of a seal carrier 3.
  • the seal carrier 3 like the inner ring 2, has a multiplicity of seal carrier segments 30 arranged adjacent to one another in the circumferential direction, wherein FIG. 1 a single seal carrier segment 30 is shown.
  • the seal carrier segment 30 carries a sealant 31 extending from a bottom of the seal carrier segment 30 in a direction away from the inner ring 2.
  • the sealing means 31 is in contact with seals 50 of a rotor of the gas turbine, not shown. By the seals 50 and the sealant 31 is a gap between the stator and the respective Leitradschaufel and the Rotor sealed.
  • two flanks extend in the radial direction, in particular in a direction facing the airfoil 10. The flanks enclose a part of the inner ring segment 20.
  • connection of the seal carrier segment 30 with the inner ring segment 20 takes place upstream (left in FIG Fig. 1 ) and downstream (right in Fig. 1 ) of the vane foot.
  • One of the two connections is a hook-type form-locking connection (left in FIG Fig. 1 ) and the other connection a wedge connection (right in Fig. 1 ).
  • the hook-type form-fitting connection is made by engaging a protrusion 35 provided on one flank of the seal carrier segment 30 into a receptacle 21 provided on the inner support segment 20.
  • the protrusion 35 extends from the flank of the seal carrier segment 30, at least substantially, parallel to the axis of the turbomachine.
  • the spline connection is made by engaging a wedge-shaped projection 22 provided on the inner ring segment 20 in a wedge-shaped receptacle 32 provided in the seal carrier segment 30.
  • a radially outer bearing surface 23 of the wedge-shaped projection 22 is formed flat and extends obliquely to a not shown axis of rotation of the gas turbine. The same applies to a radially outer bearing surface 33 of the wedge-shaped receptacle 32.
  • a radially inner bearing surface 24 of the wedge-shaped projection 22 extends, at least substantially, parallel to the axis of the gas turbine, not shown, and is planar. The same applies to a radially inner bearing surface 34 of the wedge-shaped receptacle 32nd
  • a tensioning means 41 in the form of an arcuate leaf spring serves for bracing the wedge connection.
  • the tensioning means 41 lies on the bottom of the seal carrier segment 30 and is supported as shown FIG. 2 can be seen on one side on the flank of the seal carrier segment 30 from. Further, the clamping means is supported on another side on two circumferentially spaced bushings 40 from.
  • the tensioning means 41 exerts on the seal carrier segment 30 a force which, at least substantially, is directed parallel to the axis of the gas turbine, whereby a clamping of the spline connection is achieved.
  • the seal carrier segment 30 extends in the circumferential direction so that it covers a plurality of guide vanes.
  • Inner ring segment 21 Recording in the inner ring segment 22 wedge-shaped projection 23 radially outer abutment surface of the wedge-shaped projection 24 radially inner abutment surface of the wedge-shaped projection 3 seal carrier 30

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13162302.7A 2013-04-04 2013-04-04 Agencement d'aubes directrices pour une turbomachine Withdrawn EP2787180A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13162302.7A EP2787180A1 (fr) 2013-04-04 2013-04-04 Agencement d'aubes directrices pour une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13162302.7A EP2787180A1 (fr) 2013-04-04 2013-04-04 Agencement d'aubes directrices pour une turbomachine

Publications (1)

Publication Number Publication Date
EP2787180A1 true EP2787180A1 (fr) 2014-10-08

Family

ID=48082919

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13162302.7A Withdrawn EP2787180A1 (fr) 2013-04-04 2013-04-04 Agencement d'aubes directrices pour une turbomachine

Country Status (1)

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EP (1) EP2787180A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3315728A1 (fr) * 2016-10-26 2018-05-02 MTU Aero Engines GmbH Gedämpfte leitschaufellagerung
US10858959B2 (en) 2017-06-08 2020-12-08 MTU Aero Engines AG Axially divided turbomachine inner ring
EP4001596A1 (fr) * 2020-11-23 2022-05-25 Pratt & Whitney Canada Corp. Moteur à turbine à gaz

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0696675A1 (fr) * 1994-08-10 1996-02-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes
EP1441108A2 (fr) * 2003-01-27 2004-07-28 United Technologies Corporation Amortisseur pour stator de turbomachine
US20060056963A1 (en) 2004-09-10 2006-03-16 Snecma Retaining of centring keys for rings under variable angle stator vanes in a gas turbine engine
DE102007015669A1 (de) * 2007-03-31 2008-10-02 Mtu Aero Engines Gmbh Turbomaschine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0696675A1 (fr) * 1994-08-10 1996-02-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif d'assemblage d'un étage circulaire d'aubes pivotantes
EP1441108A2 (fr) * 2003-01-27 2004-07-28 United Technologies Corporation Amortisseur pour stator de turbomachine
US20060056963A1 (en) 2004-09-10 2006-03-16 Snecma Retaining of centring keys for rings under variable angle stator vanes in a gas turbine engine
DE102007015669A1 (de) * 2007-03-31 2008-10-02 Mtu Aero Engines Gmbh Turbomaschine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3315728A1 (fr) * 2016-10-26 2018-05-02 MTU Aero Engines GmbH Gedämpfte leitschaufellagerung
US10858959B2 (en) 2017-06-08 2020-12-08 MTU Aero Engines AG Axially divided turbomachine inner ring
EP4001596A1 (fr) * 2020-11-23 2022-05-25 Pratt & Whitney Canada Corp. Moteur à turbine à gaz

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