EP2716874A1 - Stator, procédé de montage et turbomachine - Google Patents

Stator, procédé de montage et turbomachine Download PDF

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Publication number
EP2716874A1
EP2716874A1 EP12187575.1A EP12187575A EP2716874A1 EP 2716874 A1 EP2716874 A1 EP 2716874A1 EP 12187575 A EP12187575 A EP 12187575A EP 2716874 A1 EP2716874 A1 EP 2716874A1
Authority
EP
European Patent Office
Prior art keywords
ring
radially
centering
vane ring
guide
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.)
Granted
Application number
EP12187575.1A
Other languages
German (de)
English (en)
Other versions
EP2716874B1 (fr
Inventor
Joseph Tomsik
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 EP12187575.1A priority Critical patent/EP2716874B1/fr
Publication of EP2716874A1 publication Critical patent/EP2716874A1/fr
Application granted granted Critical
Publication of EP2716874B1 publication Critical patent/EP2716874B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/001—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
    • 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
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps

Definitions

  • the invention relates to a vane ring according to the preamble of patent claim 1, a method for mounting a vane ring and a turbomachine.
  • Turbomachines such as aircraft engines regularly have at least one compressor-side adjustable guide vane row with a large number of guide vanes which can be pivoted about their vertical axis in order to set optimum operating conditions.
  • the vane row forms a guide vane ring with an inner ring surrounding a rotor section.
  • the inner ring is used for internal stabilization and storage of the guide vanes and can, for example in the DE 10 2007 015 669 A1 shown to be composed of two half rings, which in turn are divided in an axial parting plane in a front half-ring segment and in a rear half-ring segment.
  • the inner ring has a plurality of bores which are arranged on the axial parting plane and in which the guide vanes dive with their bearing journals.
  • a plurality of axial pins or screws are provided, by means of which the half-ring segments are held together.
  • the pins are arranged between two adjacent bearing journals. In accordance with small engines or small Leitschaufelotti but is not sufficient space for the pins between the journals available.
  • An alternative pinning or screwing radially inward to the bearing pin leads to acentralsnachteil and unfavorable structural design of the opposite rotor section.
  • the object of the invention is to provide a vane ring for a turbomachine, which eliminates the aforementioned disadvantages and allows a compact design of a vane ring.
  • An inventive vane ring for a turbomachine has a plurality of rotatable vanes, an inner ring for radially inner stabilizing the vanes, which has two half rings, which are each separated in an axial parting plane in a front half-ring segment and in a rear half-ring segment.
  • the vane ring has an annular seal carrier having two Dichtungwaitringe, which are releasably secured to each one of the half-ring segments and are arranged with a respective body portion radially inward to the half-ring segments.
  • mold elements are used in opposite inner-ring-side recesses of the half-ring segments, which interact positively and / or non-positively with the recesses forming wall sections and which have a centering section, on each of which a guide vane is guided.
  • the form elements brace each of the two half-ring segments axially, radially and circumferentially. At the same time, they center the guide vanes over their centering section.
  • the mold elements are secured radially in their respective positions used in the recesses against falling out of the recesses. Since no installation space for axial connecting elements for connecting the half-ring segments to the respective half-ring is required between the guide vanes, the inner ring and thus the guide vane ring can be made correspondingly compact and weight-optimized.
  • the number of guide vanes can be increased. Due to the greater variability with respect to the number of guide vanes, the aerodynamics of the turbomachine can be improved.
  • the production of the recesses for the centering is carried out vorzugswan in the paired state of the half-ring segments.
  • the recesses are formed by means of electrochemical removal (ECM) or by wire erosion.
  • ECM electrochemical removal
  • the centering sections themselves are preferably produced generatively as a function of an expected load, the respective component class and permissible tolerances.
  • the mold elements each have a cuboid base body, which has a relation to a front portion and a rear portion cross-section reduced central portion.
  • the recesses are then preferably each one lying in the parting plane with respect to a recess base cross-section reduced opening portion.
  • the recesses are dovetailed, wherein they are arranged opposite with their cross-section reduced sections in the mounted state.
  • the dovetail-like recesses with the corresponding form elements allow a large force application and a secure fit.
  • the centering sections each preferably extend in a pin-like manner from the central section transversely to the cross-sectional taper and are thus positioned on the axial parting plane.
  • the guide vanes preferably each have a bearing bore for internal guidance on the respective centering section. Such a centering can be made to save space, since the centering dive into the vanes. Of course, it is also possible to perform the centering cup-like and immerse the vanes with a journal in the centering, so that the vanes are guided outside.
  • the inner ring can have vane cell bores which lie on the axial parting plane and into which the vanes with their radially inner vane plates can dip.
  • the rear half-ring segments each have a radially inwardly pointing radial flange and the seal carrier half-rings each have a radially outwardly pointing radial web which, in the mounted state flat in the plant.
  • the downstream attachment of the seal carrier on the inner ring has the advantage that there is sufficient space in this area.
  • an axial sealing surface is created by the radially located with the radial web overlapping radial flange, are effectively sealed by means of the leakage paths between the inner ring and the seal carrier.
  • an axial gap is formed between each of the radial flange and an upstream rear wall of the rear half-ring segments, and axial connecting elements for connecting the respective half-ring segments to a half-ring are inserted with their shanks in a radially inwardly open groove of the radial flanges and in an axial bore of the radial webs.
  • the connection elements are screws, which allows easy assembly and disassembly. Through the grooves in the radial flanges while assembly and component tolerances of the inner ring and the seal carrier can be compensated.
  • the mounting of the seal carrier on the inner ring can be further simplified if the connecting elements are held with their heads against rotation in the axial gap. As a result, no counter-holder is necessary when screwing a locking element such as a nut to prevent co-rotation of the connecting elements.
  • the guide vanes are mounted on the housing side with the bearing bushes used in the bearing bores.
  • the front and rear half-ring segments are arranged axially around the inner blade plates.
  • the form elements are introduced with their centering radially from the inside into the inner blade plate and inserted into the respective opposite recesses.
  • the screws are inserted radially from the inside into the slots of the radial web, wherein they are arranged with their heads in the axial gap.
  • the seal carrier half rings are pushed with their axial bores axially from behind onto the screw shafts.
  • the nuts are screwed onto the screws axially from behind and tightened with a set torque.
  • the process is simple and quick to perform. Due to the axial mounting can a radial mounting clearance between the inner ring and the seal carrier can be reduced.
  • a turbomachine according to the invention has at least one guide vane ring according to the invention. Due to the axial mounting of the inner ring and the seal carrier, a radial gap reduction between the inner ring and the seal carrier is achieved. This results in a total of less radial play. At the same time, a gap between the rotor-side sealing tips or sealing fins and the guide vane ring-side sealing elements can be reduced. In addition, leakage paths between the inner ring and the seal carrier are sealed. This results in an improved aerodynamics of the compressor and thus a higher compressor efficiency compared to a turbomachine with a conventional vane ring. In addition, the minimization of the inner ring construction space results in a weight saving and an optimized rotor construction with respect to structure and vibration behavior.
  • an inventive vane ring 1 a turbomachine such as an aircraft engine, a plurality of vanes 2, an inner ring 4, mold elements 6 and a seal carrier 8.
  • the vane ring 1 is arranged on the stator side in the compressor and surrounds a rotor drum 10 of a rotor which is in the flow direction x of a main flow extending machine axis M rotates.
  • the guide vanes 2 are adjustable about their blade axis or main axis H extending in the radial direction z and each have an airfoil 12 and an inner blade plate 14.
  • the guide vanes 2 each have a radially outer blade plate, not shown, and a radially from the outer blade plate outside extending adjusting pin, by means of which they each with a housing-side adjusting device for pivoting to cooperate about their major axis H.
  • the inner blade plates 14 are each arranged in a radial outer blind hole-like radial bores or a blade plate bore 15 of the inner ring 4. They have a radially inner and parallel to the machine axis M extending bottom 16 and a bottom 16 opposite top 18.
  • the top 18 is arranged obliquely to the machine axis M, wherein it extends in the flow direction x radially from the inside to the outside. It forms with an upstream or front annular space surface 20 of the inner ring 4, with a downstream or rear annular space 22 of the inner ring 4 and extending between the radial bores 15 and the two annular space surfaces 20, 22 in sections interconnecting not shown inner ring surfaces a radially inner side wall portion one of the main flow through the annulus.
  • the vanes 2 have in their inner blade plate 14 each designed as a blind hole bearing bore 24 which is open to the bottom 16 and is coaxial with the main axis H oriented.
  • the bearing bores 24 serve for centering the guide vanes 2 about their main axis H and are each provided with a preferably pressed-in bearing bush 28 for receiving a centering section 26 of the mold elements 6.
  • the bearing bore and / or the centering portion 26 are coated, whereby the bearing bush 28 can be omitted.
  • the inner ring 4 serves for the radially inner stabilization of the guide vanes 2 and is spaced from the rotor drum 10 via a radial gap. It consists of two halves separated in a horizontal housing separating plane, which in turn are subdivided in an axial dividing plane T into a front half-ring segment 30 and a rear half-ring segment 32. Each half-ring segment 30, 32 thus forms one half of the radial bores 15 for receiving the inner blade plates 14.
  • the front half-ring segments 30 each have a bottom surface 34 and an end face 36 orthogonal thereto.
  • the bottom surface 34 extends in the direction of the machine axis M and is disposed radially inward of the end surface 36.
  • the bottom surface 34 is downstream of a lying in the axial parting plane T trailing edge 38 (s. FIG. 2 ) of the front Half-ring segment 30 limited and penetrated by a plurality of recesses 40 for receiving one half of the mold elements 6.
  • the recesses 40 pass through the bottom surface 34 in the region of the radial bores 15 and are open to the trailing edge 38.
  • they are preferably dovetail-shaped with a base 42 which is enlarged cross-sectionally with respect to an opening 44 merging into the trailing edge 38.
  • the end face 36 extends radially outward of the bottom surface 34 and transitions into the front annulus surface 20. It has such a radial extent that in the illustrated basic position of the guide vanes 2, the upper side 18 of the inner blade plate 14 is stepless or nearly stepless and thus flush with the front annular space 20.
  • the rear half-ring segments 32 each have a bottom surface 46 and a rear surface 48 extending orthogonally to the bottom surface 46.
  • the bottom surface 46 extends in the direction of the machine axis M and is disposed radially inward of the rear surface 48. It extends downstream of a lying in the axial parting plane T leading edge 50 (s. FIG. 2 ) of the rear half-ring segment 32 and is penetrated by a plurality of recesses 52 for receiving one half of the mold elements 6.
  • the recesses 52 pass through the bottom surface 46 in the region of the radial bores 15 and are open to the front edge 50.
  • FIG. 2 Shown are preferably dovetailed with a bottom 54, which is cross-sectionally opposite to a merging into the front edge 50 muzzle 56.
  • the rear surface 48 extends radially outwardly from the bottom surface 46 in a rearward region. It merges into an axial projection 58 whose surface facing away from the rear surface 48 represents the rear annular space surface 22.
  • the radial position of the axial projection 58 is such that in the illustrated basic position of the guide vanes 2, the upper side 18 of the inner blade plate 14 is steplessly or nearly steplessly and thus flush with the rear annular space surface 22. Due to the above-described inclination of the top 18, the rear surface 48 is higher than the end face 36 is formed.
  • the rear half-ring segments 32 each have a radial flange 60 which extends radially inward from the axial projection 58.
  • the radial flange 60 is over an axial gap 62 spaced from the rear surface 48 and has a plurality of the radial flange 60 passing through in the axial direction and radially inwardly open grooves 64.
  • the axial gap 62 has an extent in the axial direction such that connecting elements 66 for connecting the seal carrier 8 to the inner ring 4 or its rear half-ring segments 32 with their heads 68 can be received therein. It is preferred if the heads 68 each interact positively with the axial projection 58 or with a portion of the seal carrier 8.
  • the grooves 64 have an extent in the circumferential direction that the connecting elements 66 can be passed with their shanks 70 therethrough.
  • the attachment elements 66 are T-bolts or screws with a flat head.
  • the mold elements 6 have, as in FIG. 2 shown, in each case a centrally tapered cuboid base body from which the centering section 26 extends.
  • the main body has two mutually remote end portions 72, 74, which are interconnected via a relative to the end portions 72. 74 cross-section reduced central portion 76.
  • the cross-sectional tapering is such that the shaped elements 6 interact positively with the dovetail-like recesses 40, 52 or with their wall sections.
  • the end portions 72, 74 are thus approximately triangular in shape, wherein they are brought together in the region of their leg tips.
  • the centering portions 26 each extend orthogonally radially outward from the reduced cross-section central portions 76. They extend centrally from the cuboid body and have for dipping into the inner paddle 14 a peg-like or cylindrical shape.
  • the seal carrier 8 is used for radial securing of the mold elements 6 in the recesses 40, 52, for carrying inlet linings 78, 80 for sealing the radial gap and for sealing leakage paths within the inner ring 4. It is divided along the horizontal housing separation plane into two seal carrier half rings, the Each have a circumferential wall 82 and a radially from the circumferential wall 82 orthogonal radially outwardly extending radial web 84.
  • the peripheral wall 82 extends in the direction of the machine axis M and is downgraded radially downstream.
  • the circumferential wall 82 is arranged in each case radially inwardly of the bottom surfaces 34, 46 of the half-ring segments 30, 32. As a result, it extends over the recesses 40, 52 of the half-ring segments 30, 32 and an accidental falling out of the mold elements 6 from the recesses 40, 52 is prevented.
  • the inlet linings 78, 80 are connected on the inner circumferential side to the circumferential wall 82. They are, for example, plate-shaped honeycomb seals and in particular cohesively connected to the circumferential wall 82, for example soldered or welded.
  • the inlet linings 78, 80 are pinned or riveted or glued to the circumferential wall 82.
  • the inlet linings 78, 80 are spaced from the rotor drum 10 in the radial direction z such that rotor-side sealing ribs or sealing fins 86 can enter them, so that the leakage path between the inner ring 4 and the rotor drum 10 is sealed.
  • the radial web 84 extends rearwardly from the inlet linings 78, 80 and has a plurality of axial bores 88 for performing the connection elements 66.
  • the radial web 84 has an end-face abutment surface 90, which can be brought into abutment with a rear abutment surface 92 of the respective radial flange 60 of the rear half-ring segments 32.
  • the vane ring 1 is thereby individually mounted for each half of the housing and closed only by the assembly of the two housing halves into a ring.
  • the bearing bushes 28 are inserted into the bearing bores 24 of the guide vanes 2, in particular pressed.
  • the guide vanes 2 are used with their adjusting pins in the housing side bearings.
  • the guide vanes 2 are now positioned like a spokes in relation to one another in the housing halves.
  • the front and rear half-ring segments 30, 32 are positioned axially about the inner paddles 14, being brought into abutment with their body edges 38, 50, and their opposed recesses 40, 52 aligned therewith.
  • the mold elements 6 are introduced with their centering portions 26 radially from the inside into the inner blade plate 14 and pressed into the opposite recesses 40, 52.
  • the connecting elements 66 are inserted radially from the inside into the grooves 64, wherein they are arranged with their heads 68 in the axial gaps 62.
  • the seal carrier half rings 8 are pushed axially with their axial bores 88 from rear to front onto the shanks 70 of the securing elements 66.
  • closing elements 94 such as nuts, are screwed axially on the shafts 70 from behind and tightened with a desired torque.
  • the guide vanes 2 are now each position-centered on a centering section 26 and the half-ring segments 30, 32 are connected to one another axially, radially and peripherally.
  • the mold elements 6 are arranged by the press-fitting into the recesses 40, 52 positively in this and additionally secured by the peripheral wall 82 of the seal carrier half rings against accidental radial falling out.
  • leakage paths between the inner ring 4 and the seal carrier 8 are closed by the sealing engagement or bracing of the front-side contact surface 90 of the seal carrier half rings with the respective rear contact surface 92 of the rear half-ring segments 32.
  • a vane ring with adjustable vanes each guided radially inward on a centering of a molding element, which is positively inserted in opposite inner ring side recesses on an axial parting plane of the inner ring, a mounting method for mounting such a vane ring 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)
EP12187575.1A 2012-10-08 2012-10-08 Stator, procédé de montage et turbomachine Active EP2716874B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12187575.1A EP2716874B1 (fr) 2012-10-08 2012-10-08 Stator, procédé de montage et turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12187575.1A EP2716874B1 (fr) 2012-10-08 2012-10-08 Stator, procédé de montage et turbomachine

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EP2716874A1 true EP2716874A1 (fr) 2014-04-09
EP2716874B1 EP2716874B1 (fr) 2017-12-27

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3056684A1 (fr) * 2015-02-16 2016-08-17 MTU Aero Engines GmbH Bague intérieure séparée axialement pour une turbomachine, un stator et groupe motopropulseur
EP3203035A1 (fr) * 2016-02-05 2017-08-09 MTU Aero Engines GmbH Système d'aube directrice d'une turbomachine
EP3460196A1 (fr) * 2017-09-20 2019-03-27 Rolls-Royce plc Ensemble de roulement pour une aube de stator variable
US10858959B2 (en) 2017-06-08 2020-12-08 MTU Aero Engines AG Axially divided turbomachine inner ring

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0546935A1 (fr) * 1991-12-11 1993-06-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stator dirigeant l'entrée de l'air à l'intérieur d'une turbomachine et procédé de montage d'une aube de ce stator
DE102008032661A1 (de) * 2008-07-10 2010-01-14 Mtu Aero Engines Gmbh Strömungsmaschine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0546935A1 (fr) * 1991-12-11 1993-06-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stator dirigeant l'entrée de l'air à l'intérieur d'une turbomachine et procédé de montage d'une aube de ce stator
DE102008032661A1 (de) * 2008-07-10 2010-01-14 Mtu Aero Engines Gmbh Strömungsmaschine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3056684A1 (fr) * 2015-02-16 2016-08-17 MTU Aero Engines GmbH Bague intérieure séparée axialement pour une turbomachine, un stator et groupe motopropulseur
US20160238028A1 (en) * 2015-02-16 2016-08-18 MTU Aero Engines AG Axially Split Inner Ring for a Fluid Flow Machine, Guide Vane Ring, and Aircraft Engine
US10294963B2 (en) * 2015-02-16 2019-05-21 MTU Aero Engines AG Axially split inner ring for a fluid flow machine, guide vane ring, and aircraft engine
EP3203035A1 (fr) * 2016-02-05 2017-08-09 MTU Aero Engines GmbH Système d'aube directrice d'une turbomachine
US10450888B2 (en) 2016-02-05 2019-10-22 MTU Aero Engines AG Guide vane system for a turbomachine
US10858959B2 (en) 2017-06-08 2020-12-08 MTU Aero Engines AG Axially divided turbomachine inner ring
EP3460196A1 (fr) * 2017-09-20 2019-03-27 Rolls-Royce plc Ensemble de roulement pour une aube de stator variable

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