EP2787176A1 - Ensemble d'aube directrice - Google Patents

Ensemble d'aube directrice Download PDF

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Publication number
EP2787176A1
EP2787176A1 EP13161906.6A EP13161906A EP2787176A1 EP 2787176 A1 EP2787176 A1 EP 2787176A1 EP 13161906 A EP13161906 A EP 13161906A EP 2787176 A1 EP2787176 A1 EP 2787176A1
Authority
EP
European Patent Office
Prior art keywords
seal carrier
segment
carrier segment
inner ring
vane assembly
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Withdrawn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
EP13161906.6A
Other languages
German (de)
English (en)
Inventor
Martin Metscher
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 EP13161906.6A priority Critical patent/EP2787176A1/fr
Publication of EP2787176A1 publication Critical patent/EP2787176A1/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Withdrawn legal-status Critical Current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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • 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

Definitions

  • the invention relates to a vane arrangement according to the preamble of claim 1.
  • Turbomachines are known from the prior art, which have an axially flow-through housing, to which at least one stator is attached, which has a plurality of adjacently arranged in the circumferential direction vanes.
  • the vanes have at their radially inner end an end portion which is connected to a seal carrier.
  • the seal carrier serves to seal a gap between the guide vanes, in particular the end sections, and a rotor of the turbomachine.
  • Guide vanes which can be adjusted about the longitudinal axis, are detachably connected at its radial end with an inner ring segment as an end portion.
  • a radially inner end of the vane for example a pin provided on the blade leaf, is received in a bush which is fixed by the inner ring segment.
  • the inner ring segment is in turn connected to a seal carrier segment.
  • the inner ring segments may move relative to the vane, particularly radially.
  • adjacent inner ring segments in particular radially, can move relative to one another in the circumferential direction.
  • a vane arrangement which has a first inner ring segment, which is connected to a first seal carrier segment, in particular detachably. Further, the vane assembly has a circumferentially adjacent second inner ring segment, which is connected to a second seal carrier segment, in particular releasably connected.
  • the first and second seal carrier segment are connected to one another at mutually facing end sides, in particular detachably connected.
  • the first and second inner ring segments are not directly connected to each other, in particular not on mutually facing end faces.
  • first and second seal carrier segment can be positively connected to each other via a one-part or multi-part coupling means.
  • the coupling means may be formed as a separate component and thus separately from the first and / or second seal carrier segment. Likewise, it may be integrally formed with one of the first and second seal carrier segments.
  • the first and / or second seal carrier segment may have on a front side a receptacle for receiving the coupling means.
  • the end faces of the first and / or second seal carrier segment are the sides which face one another in the circumferential direction.
  • Both the first and the second seal carrier segment may have two end portions, each with the aforementioned end face, which are opposite in the circumferential direction.
  • the receptacle for receiving the coupling means is at the end sides of the end portions intended.
  • a connection of the seal carrier segments can be done in a simple manner by the coupling means is inserted for example in the receptacle of the first seal carrier segment and this seal carrier segment is connected to the circumferentially adjacent second seal carrier segment, wherein the coupling means engages for producing the compound in the receptacle of the second seal carrier segment.
  • the coupling means friction, form and / or positively secured in one or both shots, in particular by a press fit, a bayonet or link closure, a locking, welding, soldering or gluing.
  • one of the first and second seal carrier segments may be connected to the inner ring segment by the coupling means.
  • the coupling of the inner ring segment with the seal carrier segment can be effected by a different coupling means than the coupling means for connecting the first seal carrier segment to the second seal carrier segment.
  • the coupling means may in particular comprise one or more bolts, in particular a bolt.
  • a bolt may be formed in profile L-shaped to allow the above-mentioned connection between the first and second seal carrier segment and the first or second seal carrier segment with the inner ring.
  • the respective seal carrier segment has correspondingly formed receptacles, so that insertion of the L-shaped bolt into this is possible.
  • a bolt may have at least one end bevel in order to be able to introduce it into the receptacle of the respective seal carrier segment in a simple manner.
  • the inner ring segment may be permanently or detachably and rigidly or movably connected to one or more guide vanes.
  • the inner ring segment may have at least one bushing which receives a radially inner journal of an airfoil of the vane.
  • the first and / or second seal carrier segment may have a bottom and at least two, in particular from the bottom, radially extending flanks. The connection of the first and / or second seal carrier segment with the respective inner ring segment and / or the connection of the first and second seal carrier segment to one another can take place via one or both flanks.
  • a sealing means such as sealing honeycomb or a brush seal, protrude in a direction facing away from the respective inner ring segment direction.
  • the sealing means may be in contact with sealing means provided on the rotor and thus seal a gap between the vane and the inner ring segment and a rotor of the turbomachine.
  • the vane arrangement described above can be used in a gas turbine, in particular an aircraft engine, with at least one compressor and / or turbine stage.
  • 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.
  • Turbomachine 1 which is shown in sections, has a plurality of impellers 2 and guide wheels 3 offset from one another in the axial direction of the turbomachine.
  • the guide wheels 3 are respectively arranged between two wheels 2 along the axial direction of the turbomachine 1 and have a plurality of guide vanes in the circumferential direction.
  • guide vanes are those which are adjustable about their longitudinal axis. In a modification, not shown, it may also be immovable vanes.
  • the vanes each have an airfoil 30 which has a pin 31 at the radially inner end.
  • the pin 31 is mounted in a bushing 33, wherein the bushing 33 is fixed by an inner ring segment 32 of an inner ring.
  • the inner ring has a plurality of circumferentially adjacent inner ring segments 32.
  • the inner ring segments 32 are formed such that they are coupled to at least one vane.
  • the inner ring segments 32 are also connected to a, in particular trough-shaped, seal carrier segment 40 of a seal carrier 4.
  • the seal carrier 4 has a plurality of circumferentially adjacent seal carrier segments 40.
  • the seal carrier segments 40 carry a sealing means 41, preferably sealing honeycomb, extending from a bottom of the seal carrier means 40 in a radial direction away from the inner ring segment 32.
  • the sealing means 41 is in contact with another sealing means formed on a rotor 10 of the turbomachine 1.
  • FIGS. 2 and 3 are circumferentially adjacent seal carrier segments 40, 40 'shown. It shows FIG. 2 an end portion of a first seal carrier segment 40 having two flanks 42, 43 extending radially from the bottom of the first seal carrier segment 40.
  • the flanks 42, 43 extend in the opposite radial direction as the sealing means 41 and serve inter alia for fastening the first seal carrier segment 40 to the associated inner ring segment 32.
  • a first flank 42 of the first seal carrier segment 40 has at the end remote from the bottom a projection 422 which extends transversely, in particular vertically, from the flank 42 '.
  • the projection 422 engages for connecting the first seal carrier segment 40 with the inner ring segment 32 in a recess provided in the inner ring segment 32 recess.
  • a second flank 43 of the first seal carrier segment 40 has at the end remote from the bottom a recess 420 which extends along the circumferential direction within the second flank 42.
  • the second flank 43 has on its front side a first receptacle 421, which extends along the circumferential direction partially within the first seal carrier segment 40.
  • the first receptacle 421 is used to receive a coupling means 5.
  • the second edge 43 has a second receptacle, not shown, for receiving the same or another coupling means 5.
  • the second receptacle is provided on the radially outer surface of the second flank 42 and thus serves to receive a coupling means 5 which extends in the radial direction.
  • the central axis of the first receptacle 421 and the central axis of the second receptacle extend transversely, in particular perpendicular, to one another.
  • first seal carrier segment 40 a coupling means 5 is inserted into the first seal carrier segment 40.
  • the coupling means 5 may have an L-shaped profile and project from the first seal carrier segment 40 both in the radial direction and in the circumferential direction.
  • the seal carrier segment 40 may have a corresponding receiving opening to the first and second receptacle (not shown).
  • two separate coupling means 5 are provided for connecting the seal carrier segment 40 with the inner ring segment 32 on the one hand and the adjacent seal carrier segment 40 ', which are each formed bolt or pin-like, in Fig. 2 only a radially projecting of the two coupling means 5 is shown.
  • the protruding region of the coupling means projecting from the first seal carrier segment 40 in the radial direction can engage in a recess in the inner ring segment 32 and thus limit or prevent a relative movement between the inner ring segment 32 and the first seal carrier segment 40 in the circumferential direction.
  • the area of the coupling means projecting from the first seal carrier segment 40 in the circumferential direction can with a receptacle 421 'in the adjacent, in FIG. 3 shown second seal carrier segment 40 'are coupled.
  • the region projecting in the circumferential direction can be frictionally connected with the receptacle 421 'and / or receptacle 421, in particular with a press fit inserted into it.
  • the area can be connected to the receptacle 421 'and / or receptacle 421 in a materially bonded manner, in particular welded, soldered or glued.
  • the area may be positively connected to the receptacle 421 'and / or receptacle 421, in particular by an outer circumference of the area engaging behind an inner circumference of the receptacle or the area being inserted in the circumferential direction into the receptacle (s), so that these a radial and axial movement of the seal carrier segments 40, 40 '(vertically or horizontally in Fig. 2, 3rd ) relative toeiander limited, preferably prevented.
  • This receptacle 421 ' is provided on an end face of an end portion of the second seal carrier segment 40'.
  • the second seal carrier segment 40 ' has the same structure as the first seal carrier segment 40, so that reference is made to the embodiments of the first seal carrier segment 40 for constructing the second seal carrier segment 40'.
  • FIG. 3 the end portion, in particular the end face of the end portion, of the second seal carrier segment 40 ' is shown, which is the in FIG. 2 opposite end face of the end portion of the first seal carrier segment 40 opposite.
  • the in FIG. 3 not shown end portion of the second seal carrier segment 40 ' may be analogous to that in FIG. 2 illustrated end portion of the first seal carrier segment 40 may be formed.
  • turbomachinery Wheel 3 stator 4 seal carrier 5 coupling means 10 rotor 30 airfoil 31 spigot 32 Inner ring segment 33 Rifle 40 first seal carrier segment 40 ' second seal carrier segment 41 sealant 42 first flank 43 second flank 420 recess 421 first receptacle of the first seal carrier segment 421 ' Receiving the second seal carrier segment 422 head Start

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13161906.6A 2013-04-02 2013-04-02 Ensemble d'aube directrice Withdrawn EP2787176A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13161906.6A EP2787176A1 (fr) 2013-04-02 2013-04-02 Ensemble d'aube directrice

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13161906.6A EP2787176A1 (fr) 2013-04-02 2013-04-02 Ensemble d'aube directrice

Publications (1)

Publication Number Publication Date
EP2787176A1 true EP2787176A1 (fr) 2014-10-08

Family

ID=48013851

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13161906.6A Withdrawn EP2787176A1 (fr) 2013-04-02 2013-04-02 Ensemble d'aube directrice

Country Status (1)

Country Link
EP (1) EP2787176A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2580249C1 (ru) * 2015-03-17 2016-04-10 Открытое акционерное общество "Авиадвигатель" Статор компрессора газотурбинного двигателя

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0384166A2 (fr) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Construction de diaphragme de compresseur
WO2011018413A1 (fr) 2009-08-08 2011-02-17 Alstom Technology Ltd Diaphragmes de turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0384166A2 (fr) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Construction de diaphragme de compresseur
WO2011018413A1 (fr) 2009-08-08 2011-02-17 Alstom Technology Ltd Diaphragmes de turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2580249C1 (ru) * 2015-03-17 2016-04-10 Открытое акционерное общество "Авиадвигатель" Статор компрессора газотурбинного двигателя

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Owner name: MTU AERO ENGINES GMBH

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