EP2725200B1 - Stator et turbomachine - Google Patents

Stator et turbomachine Download PDF

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Publication number
EP2725200B1
EP2725200B1 EP12189935.5A EP12189935A EP2725200B1 EP 2725200 B1 EP2725200 B1 EP 2725200B1 EP 12189935 A EP12189935 A EP 12189935A EP 2725200 B1 EP2725200 B1 EP 2725200B1
Authority
EP
European Patent Office
Prior art keywords
guide vane
connection
ring
segments
vane ring
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.)
Active
Application number
EP12189935.5A
Other languages
German (de)
English (en)
Other versions
EP2725200A1 (fr
Inventor
Georg Zotz
Hermann Becker
Vitalis Mairhanser
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 EP12189935.5A priority Critical patent/EP2725200B1/fr
Publication of EP2725200A1 publication Critical patent/EP2725200A1/fr
Application granted granted Critical
Publication of EP2725200B1 publication Critical patent/EP2725200B1/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
    • 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
    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • the invention relates to a guide vane ring according to the preamble of patent claim 1 and a turbomachine.
  • Turbomachines such as aircraft engines and stationary gas turbines, regularly have at least one compressor-side adjustable guide vane row with a plurality of guide vanes which can be pivoted about their main axis or vane axis for setting optimum operating conditions.
  • the adjustable vane row forms with a rotor portion enclosing an inner ring a vane ring.
  • the inner ring serves for internal stabilization and storage of the guide vanes. He can be like in the EP 0 947 668 B1 shown, a plurality of radial bearing bores for receiving a respective blade-side journal.
  • the inner ring consists of several ring segments, which are interconnected via a radially inner seal carrier.
  • the seal carrier consists of semicircular carrier segments which are pushed onto the ring segments during assembly in the circumferential direction.
  • the carrier segments are braced together after positioning on the inner ring via circumferentially oriented and located in the hot gas path clamping screws.
  • a radial gap to the rotor portion of the seal carrier is provided on its side facing away from the vanes inner peripheral surface with a plurality of inlet linings, enter into the rotor-side sealing fins or sealing tips.
  • the installation of the clamping screws is very complex. In addition, the clamping screws require a lot of space and can be sucked in the accidentally released state in the hot gas path.
  • An inventive vane ring for a turbomachine has a plurality of rotatable vanes, a static inner ring for radially inner stabilization of the vanes, which consists of at least two ring segments is assembled, and a seal carrier having at least two support segments slidable on the ring segments and which is provided with sealing elements for sealing a radial gap between the inner ring and an opposite rotor section.
  • connecting devices are provided for the automatic connection of adjacent carrier segments in the area of parting lines, each of which has at least two cooperating connecting elements, of which one connecting element is formed on one end of the carrier segment and the corresponding connecting element on the adjacent carrier segment on the other side.
  • the carrier segments are mutually centered and a mounting clearance between the inner ring and the seal carrier eliminated.
  • the one connecting elements are in the circumferential direction of the vane ring protruding from the carrier segment connecting tongues and the corresponding connecting elements each have a peripheral contact surface of the adjacent carrier segment for conditioning the connecting tongue.
  • connections of the carrier segments in the radial direction can be additionally stabilized if the connecting tongues in the unassembled state of adjacent carrier segments lie radially inward to the contact surfaces. As a result, the connecting tongues brace the carrier segments in the mounted state in the radial direction.
  • the respective connecting tongue can additionally be formed as a sealing element.
  • An effective sealing of the respective parting line can be achieved in that the connecting tongues are plate-like and extend substantially each over an entire axial length of the parting line.
  • connection tongues are a metal sheet fastened to the support segments.
  • connection tongues are produced separately from the carrier segment and are subsequently connected to the respective carrier element, for example by means of a fluid connection such as welding or soldering.
  • the separate production prevents the geometry and production of the carrier segments from having to be changed.
  • the connecting devices can be retrofitted as a retrofit kit for existing vane rings by the separate production.
  • the connection tongues can also be designed as an integral component section of the respective carrier segment.
  • the connecting devices are in the mounted state the guide vane ring preferably each arranged in a closed in the axial and radial direction of the vane ring cavity between the inner ring and the seal carrier.
  • Threading the connecting tongues into the cavities and thus mounting the seal carrier can be simplified if the connecting tongues are cross-sectionally tapered at their free end in the transverse direction.
  • a turbomachine according to the invention has at least one guide vane ring according to the invention. Due to the concentric position of the sealing elements to the opposite rotor section, such a turbomachine is characterized by a higher compressor efficiency and an upwardly shifted surge line than a turbomachine with a conventional vane ring.
  • the connecting means act simultaneously as radial seals, a leakage flow through joints between adjacent seal carrier segments therethrough prevented, which also has a positive effect on the compressor efficiency and the surge limit.
  • an inventive vane ring 1 a turbomachine such as an aircraft engine at least a plurality of vanes 2, an inner ring 4, a seal carrier 6 and in a joint area of the seal carrier 6 each have a connection means 8.
  • the vane ring 1 is the stator side in the compressor of the turbomachine arranged and engages around a rotor portion 10 of a rotor which rotates about a m in the flow direction x of a main flow extending machine axis m.
  • the guide vanes 2 are adjustable about their main axis h extending radially to the machine axis m and each have an airfoil 12, an inner paddle 14 and a bearing journal 16 extending radially inwardly from the paddle 14.
  • the guide vanes 2 each have an outer, not shown Bucket plate and a radially outwardly extending from the outer blade plate adjusting pin, which cooperates with a housing-side adjusting device.
  • the inner blade plates 12 are each arranged in a radially outer countersunk portion 18 of the inner ring 4 passing through bearing bore 20. They have a radially inner and extending along the machine axis m bottom 22 and an opposite bottom 22 to the top 24.
  • the top 24 is arranged obliquely to the machine axis m, wherein it extends radially in the flow direction x from inside to outside. It forms in an unadjusted position with an inner ring surface 26 a step-free or almost step-free radially inner side wall portion of a flowed through by the main flow annulus.
  • the inner ring 4 serves for the radially inner stabilization or support of the guide vanes 2. It has the bearing bores 20 and the inner ring surface 26 and is spaced from the rotor section 10 via a radial gap. It consists of two half rings, each with an arc section of 180 °, which are assembled in the region of a horizontal parting plane of a machine housing of the turbomachine to the inner ring 4. Of course, a stronger segmentation of the inner ring 4 is possible beispielsweie in four ring segments.
  • the bearing bores 20 respectively pass through the inner ring surface 26 in the radial direction. They each have a radially inner bearing portion 28 for receiving bushings 30 and the radially outer countersink portion 18 for receiving the inner paddle 14th
  • the bushings 30 are inserted radially from the inside out into the bearing sections 28. They each have a T-shaped cross section with a radially expanded outer collar 32, by means of which they rest in each case on a radially inner peripheral surface 34 of the half rings.
  • the guide vanes 2 dive with their bearing pins 16 in the bearing bushes 30 and are thus rotatably guided relative to their main axis h in the radial direction.
  • a sliding disk may be screwed onto the bearing journal 16, which in the installed state is arranged between the bearing bushes 30 and the inner blade plates 14 and defines a sliding surface for the guide blades 2.
  • the inner ring surface 26 extends downstream of the bearing bores 20 via a rear and obliquely to the machine axis m radially from inside to outside employed axial projection 36 of the inner ring 4. Between the axial projection 36 and the blades 12 is formed in each case a radial so-called flag gap 38, to achieve a high efficiency of the turbomachine and a high surge limit is minimized.
  • a flag gap 38 to achieve a high efficiency of the turbomachine and a high surge limit is minimized.
  • at least some of the guide vanes 2 are mechanically coupled to the inner ring 4 or the half-ring in the radial direction. The mechanical coupling can take place or by means of axial locking pins which pass through at least one side in inner ring 4 and engage in a corresponding annular groove of the bearing pin 16.
  • the inner ring 4 has a front end-side guide groove 40 and a rear axial guide projection 42, which are each arranged radially inwardly of the inner ring surface 26.
  • the seal carrier 6 is used for positioning inlet pads 44, 46 for sealing the radial gap between the rotor section 10 and the inner ring 4. It is radially inwardly disposed on the inner ring 4 in a form-fitting manner. He has, as in FIG. 2 shown, preferably two semi-circular support segments 48, 50 which are pushed in the circumferential direction on the ring segments.
  • the carrier segments 48, 50 define in the assembled state of the seal carrier 6 separating joints 52, which lie in only two carrier segments 48, 50 preferably in the horizontal parting plane of the machine housing.
  • the carrier segments 48, 50 each have a U-shaped profile with a viewed in the flow direction x front wall 54, a rear wall 56 and the two walls 54, 56 interconnecting circumferential wall 58th
  • the front walls 54 of the support segments 48, 50 each have a front downstream circumferential projection 60 and the rear walls 56 each have a laterally and upstream opened circumferential groove 62.
  • the peripheral projections 60 engage positively in the front guide grooves 40 of the half rings of the inner ring 4.
  • the rear guide projections 42 of the half rings of the inner ring 4 engage in a positive fashion in the circumferential grooves 58. To enable assembly these form-fitting connections are subject to play.
  • the inlet pads 44, 46 are inter alia on the inner peripheral side on the circumferential wall 58 and on the other inner peripheral side on a radially inner and rear circumferential extension 64 opposite rotor-side sealing tips or sealing fins 66 on the peripheral wall 58.
  • the connecting devices 8 are respectively arranged on the end side of the carrier segments 48, 50 and thus in the assembled state in the region of the parting lines 52. They are positioned in cavity 68 between the inner ring 4 and the seal carrier 6.
  • the cavity 68 is bounded in the radial direction by the half rings and the peripheral wall 58 of the carrier segments 48, 50 and in the axial direction by the front wall 54 and the rear wall 56 of the carrier segments 48, 50.
  • the connecting devices 8 each have two automatically cooperating connecting elements 70, 72.
  • "Automatically or automatically” in the sense of the invention means that when assembling the carrier segments 48, 50 or when mounting or closing the machine housing, the cooperating connecting elements 70, 72 of the connecting devices 8 in each case without further measures with each other.
  • one connecting element is in each case a connecting tongue 70 and the connecting element corresponding thereto a contact surface 72.
  • the connecting tongues 70 and the contact surfaces 72 are each formed on opposite end sections of the adjacent carrier segments 48, 50. In the case of only two carrier segments 48, 50, these can be provided at their one end section with a connecting tongue 70 and at their other end section with a contact surface 72.
  • one carrier segment 48 may each have a connecting tongue 70 at its two end sections and the other carrier segment 50 may each have a contact surface 72 at its two end sections.
  • a connecting tongue 70 is arranged on one end section of the carrier segment 48 and a contact surface 72 on the opposite end section of the adjacent carrier segment 50.
  • the connecting tongue 70 is in the embodiment shown, a plate-like metal sheet, which is arranged between the walls 54, 56 on the outer peripheral side of the peripheral wall 58. It extends over the entire extent of the circumferential wall 58 in the direction of the machine axis m and thus substantially over the entire axial length of the respective parting line 52. As a result, the parting line 52 is radially closed, so that the formation of a radial leakage flow is effectively prevented.
  • the support segments 48, 50 stabilized in the axial direction of the vane ring 1 and relative axial displacements of the support segments 48, 50 to each other prevented, since the connecting tongue 70 laterally against the walls 54, 56 and spaced only in a minimum mounting distance therefrom is.
  • the connecting tongue 70 has a fastening portion 74, by means of which it is fastened to a peripheral surface of the peripheral wall 58 facing the inner ring 4 in the assembled state and a connecting portion 78 for engagement with the contact surface 72 of the adjacent support segment 50.
  • the connecting portion 78 projects circumferentially over the latter Carrier segment 50 and thus extends over the parting line 52 on the adjacent support segment 50.
  • 50 may alternatively or additionally be the connecting tongue 70 in the unassembled state of the vane ring radially inward to the contact surface 72.
  • the contact surface 72 is arranged on the outer peripheral side on the peripheral wall 58 of the adjacent carrier segment 50. It extends over the entire axial extension of the peripheral wall 58 and performs an outer contour of the peripheral wall 58 unchanged.
  • the contact surface 72 may be tangential or wedge-shaped, for example in the circumferential direction, wherein the radial thickness of the peripheral wall in the direction of Dividing line 52 reduced.
  • the connecting tongues 70 as in FIG. 2 shown, two each in the sliding direction or in the mounting direction opposite to each other employed guide surfaces 82, 84 have, so that the connecting tabs 72 are cross-sectionally tapered head side in the transverse direction, ie in the direction of the machine axis m.
  • the connecting portions 78 each at their own in the transverse direction extending sides concave recesses 86, 88, each forming a space for receiving the collar 32 of the bushings 30.
  • connection tabs 70 are flat against the contact surfaces 72 and thus cause a centering of the adjacent support segments 48, 50 to each other, a removal of mounting clearance, a concentric arrangement of the seal carrier 6 and the inner ring 4 to the rotor and prevent radial displacement and axial displacement of Carrier segments 48, 50 relative to each other.
  • the parting lines 52 are radially sealed by the connection tongues 70, so that the formation of a leakage current between the adjacent support segments 48, 50 is effectively prevented.
  • the support segments 48, 50 of the seal carrier 6 with the half rings of the inner ring 4 by radial screws 90 may be interconnected, which are guided by the rear guide projections 42 and are screwed into holes 92 of the rear wall 56.
  • a vane ring for a turbomachine which has a connection means for automatically connecting adjacent support segments having at least two cooperating connecting elements, of which one connecting element end side to the one support segment and the corresponding connecting elements end is formed on the adjacent carrier segment, and a turbomachine with such a vane ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Couronne d'aubes directrices (1), destinée à une turbomachine, comprenant une pluralité d'aubes directrices rotatives (2), une bague intérieure fixe (4) destinée à la stabilisation radialement intérieure des aubes directrices (2), laquelle est constituée d'au moins deux segments de bague, et un support de garniture d'étanchéité (6) comportant au moins deux segments de support (48, 50) pouvant coulisser sur les segments de bague et des éléments d'étanchéité (44, 46) destinés à assurer l'étanchéité d'un interstice radial ménagé entre la bague intérieure (4) et une partie de rotor opposée (10), la couronne d'aubes directrices comportant un moyen de liaison (8) destiné à relier automatiquement des segments de support (48, 50) adjacents dans la région de joints de séparation (52), caractérisée en ce que l'élément de liaison comporte au moins deux éléments de liaison (70, 72) coopérant, dont l'un des éléments de liaison (70, 72) est formé du côté extrémité sur l'un des segments de support (48, 50) et l'élément de liaison (72, 70) correspondant est formé du côté extrémité sur le segment de support (50, 48) adjacent.
  2. Couronne d'aubes directrices selon la revendication 1, dans laquelle certains éléments de liaison (70, 72) sont chacun une languette de liaison (70) faisant saillie du segment de support (48, 50) dans la direction circonférentielle de la couronne d'aubes directrices (1) et les éléments de liaison correspondants sont chacun une surface d'appui périphérique (72) du segment de support (50, 48) adjacent destinée à l'appui de la languette de liaison (70).
  3. Couronne d'aubes directrices selon la revendication 2, dans laquelle, lorsque des segments de support (48, 50) adjacents sont à l'état non assemblé, les languettes de liaison (70) se trouvent radialement à l'intérieur par rapport aux surfaces d'appui (72).
  4. Couronne d'aubes directrices selon la revendication 2 ou 3, dans laquelle les languettes de liaison (70) sont en forme de plaque et s'étendent chacune sensiblement sur toute la longueur axiale du joint de séparation (52).
  5. Couronne d'aubes directrices selon l'une des revendications 2, 3 ou 4, dans laquelle les languettes de liaison (70) sont chacune une tôle fixées à l'un des segments de support (48, 50).
  6. Couronne d'aubes directrices selon l'une des revendications précédentes, dans laquelle, lorsque la couronne d'aubes directrices (1) est à l'état monté, les moyens de liaison (8) sont disposés dans une cavité (68) fermée dans une direction axiale et radiale de la couronne d'aubes directrices (1) et ménagée entre la bague intérieure (4) et le support de garniture d'étanchéité (6).
  7. Couronne d'aubes directrices selon l'une des revendications 2 à 6, dans laquelle les languettes de liaison (70) sont effilées en coupe transversale dans la direction transversale à leur extrémité libre.
  8. Turbomachine comprenant au moins une couronne d'aubes directrices (1) selon l'une des revendications précédentes.
EP12189935.5A 2012-10-25 2012-10-25 Stator et turbomachine Active EP2725200B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12189935.5A EP2725200B1 (fr) 2012-10-25 2012-10-25 Stator et turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12189935.5A EP2725200B1 (fr) 2012-10-25 2012-10-25 Stator et turbomachine

Publications (2)

Publication Number Publication Date
EP2725200A1 EP2725200A1 (fr) 2014-04-30
EP2725200B1 true EP2725200B1 (fr) 2018-06-06

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Family Applications (1)

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EP12189935.5A Active EP2725200B1 (fr) 2012-10-25 2012-10-25 Stator et turbomachine

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EP (1) EP2725200B1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3176386B1 (fr) 2015-12-04 2021-01-27 MTU Aero Engines GmbH Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
EP3176384B1 (fr) * 2015-12-04 2023-07-12 MTU Aero Engines AG Virole interne, secteur de virole interne, aubage statorique et turbomachine
EP3379037B1 (fr) * 2017-03-23 2021-06-02 MTU Aero Engines AG Étanchéité sur une bague intérieure d'une couronne d'aubes directrices
US11725533B2 (en) * 2020-11-10 2023-08-15 Pratt & Whitney Canada Corp. Variable guide vane assembly and bushing ring therefor

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
FR2775731B1 (fr) 1998-03-05 2000-04-07 Snecma Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison
FR2824593B1 (fr) * 2001-05-10 2003-07-18 Snecma Moteurs Agencement de support de pivots d'aubes de stator a deux parties d'anneau liees par un element interne
US7510369B2 (en) * 2005-09-02 2009-03-31 United Technologies Corporation Sacrificial inner shroud liners for gas turbine engines
DE102006024085B4 (de) 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise
US8500394B2 (en) * 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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