EP2379847A1 - Procédé de montage d'une bague intérieure intégrée d'un stator de turbocompresseur - Google Patents

Procédé de montage d'une bague intérieure intégrée d'un stator de turbocompresseur

Info

Publication number
EP2379847A1
EP2379847A1 EP10702397A EP10702397A EP2379847A1 EP 2379847 A1 EP2379847 A1 EP 2379847A1 EP 10702397 A EP10702397 A EP 10702397A EP 10702397 A EP10702397 A EP 10702397A EP 2379847 A1 EP2379847 A1 EP 2379847A1
Authority
EP
European Patent Office
Prior art keywords
inner ring
radius
ring
outer radius
vane
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
EP10702397A
Other languages
German (de)
English (en)
Other versions
EP2379847B1 (fr
Inventor
Frank Stiehler
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 GmbH
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 GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2379847A1 publication Critical patent/EP2379847A1/fr
Application granted granted Critical
Publication of EP2379847B1 publication Critical patent/EP2379847B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the invention relates to a method for mounting an integral inner ring of a turbocompressor stator to a vane ring.
  • the vanes are mounted on a rotatable ring.
  • the inner ring is provided with openings (bearing countersinks) into which bearing bushes for the inner pins of the guide vanes can be inserted. Only when the guide vanes are inserted in the compressor housing, the installation (assembly) of the inner ring takes place.
  • assembly has hitherto been possible only in segments.
  • the inner ring is divided circumferentially into individual segments with a center angle ⁇ 180 °, and the segments with the openings are individually “threaded" into the inner lugs of the vanes, as far as the gaps between the segments allow. In practice, therefore, the segments typically have a midpoint angle not greater than 30 °.
  • Such a segmented inner ring is shown, for example, in EP 1 508 672 A1.
  • a method for mounting a segmented inner ring without axial division is known from DE 10 2006 024 085 Al. The method described therein makes use of the fact that the openings in the segments of the inner ring are significantly larger in diameter than the inner cones of the guide vanes, so that the latter can be temporarily positioned eccentrically and obliquely in the openings.
  • segmented inner rings have fundamental disadvantages compared to one-piece, closed (integral) inner rings.
  • the segmentation leads to greater wear and a significantly shorter service life.
  • the segmentation leads to an undesirable cluster swing.
  • the inventive method for mounting an integral inner ring of a turbocompressor stator to a vane ring comprises the following steps:
  • the invention is based on the recognition that an integral inner ring can be designed so deformable that the inner ring can be biased with a suitable geometric design of its openings and the inner pins of the vanes so that the Verforrmingshunt of the inner ring during its relaxation for threading the inner ring in the Guide vane ring can be used.
  • the die ensures that no overstretching of the inner ring occurs because it limits the bend to a defined radius.
  • Figure 1 is a plan view of a die and a part of an inner ring before its pre-bending
  • Figure 2 is a schematic partial view of a vane ring with one side attached inner ring
  • Figure 3 is a larger schematic partial view of the vane ring with partially threaded inner ring.
  • FIG. 4 shows the geometric model on which the method according to the invention is based.
  • an integral, that is undivided, one-piece inner ring 10 is provided with an outer radius R which is constant over the circumference.
  • a one-piece inner ring is to be understood here also a one-piece part ring with a center angle> 180 °.
  • the outer radius R of the inner ring 10 corresponds to an inner radius S of the Leitschaufelkranzes 12, to which the inner ring 10 is to be mounted.
  • the vane ring 12 is the entirety or, as described in the following assembly process, a part of the inner ring 10 to be held vanes 14, which are already pre-assembled in the tubular housing or in a housing part of the compressor.
  • the vane ring 12 is in the latter case a partial ring (preferably with a midpoint angle ⁇ 180 °) of circumferentially juxtaposed vanes 14.
  • the vanes 14 have inner pins 16 which are to be stored in associated openings 18 (bearing depressions) of the inner ring 10.
  • the inner ring 10 is pre-bent by the inner ring 10 constant to an outer radius r is biased, which is smaller than the outer radius R of the inner ring 10 in the untensioned state.
  • the bias is applied over the entire circumference of the inner ring 10 or over a certain part, preferably over a part whose arc length of the arc length of the preassembled vane ring 12 corresponds (based on the radii R and S).
  • the inner ring 10 is brought into contact with the die 20 at an inner contact point A for this purpose.
  • the inner ring 10 is fixed with a clamping 22 with adjustable drawbar.
  • two further adjustable clamping units 24 are provided with which at two points of pull, which are preferably diametrically opposed to each other (center angle distance ⁇ 180 °), the inner ring 10 is bent onto the die 20.
  • the clamping units 24 may - according to the example shown in Figure 1 - train bearing forming pins 26 and / or claws on which a tensile force is applied.
  • the clamping direction S is adjusted during pretensioning so that the inner ring 10 does not buckle, but applies uniformly to the die 20.
  • the clamping units 22 and 24 are then fixed, so that the inner ring 10 remains in its prestressed state.
  • Figures 2 and 3 show schematically how subsequently the inner ring 10 is threaded by relaxing on its original outer radius R in the vane part ring.
  • the biased inner ring 10 is attached to one end 28 of the vane ring 12 and unrolled in the vane ring 12 by the adjustable clamping units 22 and 24 are relieved (release of the fixation).
  • the openings 18 of the inner ring 10 are moved without tilting or jamming over the inner pins 16 of the guide vanes 14. This is possible in the particular relaxation restoring deformation of the inner ring 10 to its original outer radius R alone due to the play of the openings 18.
  • FIG. 3 shows how, at the tangential contact point P, the outer radius of the inner ring without transition from the smaller radius r (pretensioned) changes directly to the original radius R (relaxed).
  • the disassembly of the inner ring 10 from the vane ring 12 is also possible by tilting or jamming by reversing the described assembly process.

Landscapes

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

Abstract

L'invention concerne un procédé de montage d'une bague intérieure intégrée (10) d'un stator de turbocompresseur sur une couronne d'aubes directrices (12), consistant à fournir la couronne d'aubes directrices (12) ayant un rayon intérieur (S); à fournir la bague intérieure (10) ayant un rayon extérieur (R) correspondant au rayon intérieur (S); à serrer la bague intérieure (10) à un rayon extérieur (r) inférieur au rayon extérieur (R) de la bague intérieure (10) non précontrainte; et à détendre la bague intérieure (10) au rayon extérieur (R).
EP10702397.0A 2009-01-16 2010-01-14 Procédé de montage d'une virole intérieure intégrée d'un stator de turbocompresseur Active EP2379847B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009004934.7A DE102009004934B4 (de) 2009-01-16 2009-01-16 Verfahren zur Montage eines integralen Innenrings eines Turboverdichterstators
PCT/DE2010/000023 WO2010081468A1 (fr) 2009-01-16 2010-01-14 Procédé de montage d'une bague intérieure intégrée d'un stator de turbocompresseur

Publications (2)

Publication Number Publication Date
EP2379847A1 true EP2379847A1 (fr) 2011-10-26
EP2379847B1 EP2379847B1 (fr) 2013-06-12

Family

ID=41796410

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10702397.0A Active EP2379847B1 (fr) 2009-01-16 2010-01-14 Procédé de montage d'une virole intérieure intégrée d'un stator de turbocompresseur

Country Status (5)

Country Link
US (1) US8943689B2 (fr)
EP (1) EP2379847B1 (fr)
CA (1) CA2746134C (fr)
DE (1) DE102009004934B4 (fr)
WO (1) WO2010081468A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2520769A1 (fr) 2011-05-02 2012-11-07 MTU Aero Engines GmbH Anneau intérieur pour la formation d'une couronne d'aube directrice, couronne d'aube directrice et turbomachine
EP2725202A1 (fr) 2012-10-25 2014-04-30 MTU Aero Engines GmbH Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine
EP2884054A1 (fr) 2013-12-10 2015-06-17 MTU Aero Engines GmbH Aube de guidage variable avec cône tronqué dans un ensemble palier
DE102014205986B4 (de) 2014-03-31 2021-03-18 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
AU2020258963A1 (en) * 2019-04-16 2021-07-29 Atlas Copco (Wuxi) Compressor Co., Ltd. Guide device for directing gas through
FR3122668B1 (fr) * 2021-05-04 2023-05-26 Safran Aircraft Engines Procédé de montage d’un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d’un organe de turbomachine

Family Cites Families (18)

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Publication number Priority date Publication date Assignee Title
BE669777A (fr)
DE892046C (de) * 1953-08-20 Maschinenfabrik Augsburg-Nürnlberg A. G., Augsburg Leitapparat für axial durchströmte Kreiselradmaschinen
DE969599C (de) * 1943-05-27 1958-06-19 Holzwarth Gasturbinen G M B H Gekuehlter Duesenkoerper fuer Kreiselmaschinen, insbesondere Abgasturbinen
DE807572C (de) * 1947-11-19 1951-07-02 Cem Comp Electro Mec Leitschaufelanordnung fuer Dampf- und Gasturbinen
FR1145011A (fr) * 1955-04-05 1957-10-21 Maschf Augsburg Nuernberg Ag Dispositif d'aubes directrices pour machines à rotor à courant axial, notamment turbines à vapeur et à gaz
NL243359A (fr) * 1958-11-07
DE1096921B (de) * 1959-08-18 1961-01-12 Licentia Gmbh Mehrstufige Axial-Dampf- oder -Gasturbine in Topfgehaeuse
US3156970A (en) * 1961-07-14 1964-11-17 Gen Motors Corp Torque converter elements and methods of making the same
US3132842A (en) 1962-04-13 1964-05-12 Gen Electric Turbine bucket supporting structure
DE1172900B (de) * 1962-04-17 1964-06-25 Gasturbinenbau Veb Verfahren zum Zusammenbau einer mehrstufigen Axialstroemungsmaschine
FR1373359A (fr) * 1962-10-19 1964-09-25 Ass Elect Ind Diaphragmes d'étage intermédiaire pour turbines et compresseurs axiaux
US3300180A (en) * 1964-11-17 1967-01-24 Worthington Corp Segmented diaphragm assembly
DE2152365C3 (de) 1971-02-03 1973-12-06 Carrier Corp., Syracuse, N.Y. (V.St.A.) Einrichtung zum Lagern der inneren Enden von drehbar gelagerten Leitschaufeln einer Axial Stromungs maschine
US3969805A (en) 1974-12-23 1976-07-20 The Trane Company Method of constructing an axial flow fan
US5086560A (en) * 1990-01-24 1992-02-11 Glazier Stephen C Method of assembling prestressed frictionless bearings
EP1508672A1 (fr) 2003-08-21 2005-02-23 Siemens Aktiengesellschaft Anneau de fixation segmenté pour une turbine
FR2870309B1 (fr) * 2004-05-17 2006-07-07 Snecma Moteurs Sa Procede d'assemblage de disques aubages monoblocs et dispositif d'amortissement des vibrations des aubes de ces disques
DE102006024085B4 (de) 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise

Non-Patent Citations (1)

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Title
See references of WO2010081468A1 *

Also Published As

Publication number Publication date
WO2010081468A1 (fr) 2010-07-22
CA2746134A1 (fr) 2010-07-22
DE102009004934A1 (de) 2010-08-19
DE102009004934B4 (de) 2021-08-26
US20110265328A1 (en) 2011-11-03
US8943689B2 (en) 2015-02-03
EP2379847B1 (fr) 2013-06-12
CA2746134C (fr) 2017-01-03

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