EP1721063B1 - Turbomachine et procede pour adapter le stator et le rotor d'une turbomachine - Google Patents

Turbomachine et procede pour adapter le stator et le rotor d'une turbomachine Download PDF

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Publication number
EP1721063B1
EP1721063B1 EP04765196A EP04765196A EP1721063B1 EP 1721063 B1 EP1721063 B1 EP 1721063B1 EP 04765196 A EP04765196 A EP 04765196A EP 04765196 A EP04765196 A EP 04765196A EP 1721063 B1 EP1721063 B1 EP 1721063B1
Authority
EP
European Patent Office
Prior art keywords
rotor
stator
axis
rotation
turbomachine
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.)
Expired - Fee Related
Application number
EP04765196A
Other languages
German (de)
English (en)
Other versions
EP1721063A1 (fr
Inventor
Tilmann Haug
Hans-Georg Lehmann
Ansgar Zoller
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.)
Mercedes Benz Group AG
Original Assignee
Daimler 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 Daimler AG filed Critical Daimler AG
Publication of EP1721063A1 publication Critical patent/EP1721063A1/fr
Application granted granted Critical
Publication of EP1721063B1 publication Critical patent/EP1721063B1/fr
Expired - Fee Related 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/052—Axially shiftable rotors
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to a turbomachine according to the preamble of patent claim 1 and to a method for adapting the stator and rotor of a turbomachine according to the preamble of patent claim 4.
  • turbomachines have both on the blades of their rotor and on the wall of their stator coatings that are abradable and relatively complex. These coatings are applied to match the rotor and stator and to reduce the gap size between the blades of the rotor and the wall of the stator.
  • EP 1 312 760 A2 is a turbomachine, in particular a gas turbine with a rotor and a stator known.
  • the wall of the stator is coated with an inlet lining.
  • the blades of the rotor have an abradable coating in which arbitrarily abrasive Al 2 O 3 or SiC particles are embedded in such a way that during the rotation of the blade tips they wear the inlet lining unevenly abrasive. Due to the abrasive removal of the inlet lining, the arbitrarily deposited Al 2 O 3 or SiC particles break off in the abradable coating.
  • the present invention is based on this prior art, the task of specifying a turbomachine and to provide a method for adjusting the stator and rotor of a turbomachine in which the gap size between the stator and rotor is minimized.
  • This embodiment has the advantage that the efficiency of the turbomachine is increased by reducing the gap size between the stator and rotor.
  • the flow machine according to the invention ensures a nearly uniform removal of the inlet lining by the rotor blades of the rotor.
  • This has the advantage that the blades of the rotor transmit lower torques to the stator. A reduced bending and upsetting of the rotor is the result. Overall, therefore, the occurring dynamic deformations acting on the blades of the rotor, noticeably reduced.
  • the means for parallel displacement and rotation of the axis of rotation of the rotor can be made for example of a modified commercial plain bearing.
  • Such plain bearings have a rotor which rotates in a housing internally coated with a bearing layer. Between bearing layer and rotor is a gap, the so-called. Lager Kunststoff, which is usually filled with liquid, usually oil.
  • the gap width varies depending on the intended use of the plain bearing between 50 and 500 microns, usually between 100 and 300 microns. If the liquid is completely or partially removed, the rotor and with it its axis of rotation due to the centripetal force is offset parallel to the axis of symmetry of the housing. The extent of dislocation increases with the amount of liquid removed.
  • the turbomachine only one rotor has to be mounted axially symmetrically on the rotor and the modified sliding bearing must be positioned axially symmetrically with respect to a stator. Thereafter, the rotor, respectively rotor, is set in rotation and carries off a part of the inlet lining. Finally, the rotor can be centered by refilling the bearing clearance of the plain bearing.
  • turbomachine according to the invention is that in comparison to conventional turbomachines an abradable coating on the rotor blade tips of the rotor can be saved. This eliminates due to the free rotation of the rotor in an excessively coated with inlet lining wall of the stator, the application of the squelch coating on the blade tips and a finishing of this squint.
  • the inventive device of the turbomachine has a robust design in terms of manufacturing tolerances, since a classification of components with respect to the Passungslage is required to a reduced extent.
  • the parallel offset of the axis of rotation of the rotor to the axis of symmetry of the stator causes the possibly occurring manufacturing tolerances, in particular the inner diameter of the stator and / or the inlet lining on the wall of the stator, can be compensated.
  • the device preferably displaces the axis of rotation of the rotor in such a way that the rotor can be introduced concentrically into the wall of the stator coated with inlet lining.
  • the axis of symmetry of the inlet lining-coated wall of the stator is offset parallel to the axis of symmetry of the stator bore in the stator housing.
  • the parallel displacement and rotation means may displace the rotor within the oversize internally coated stator such that the axis of rotation of the rotor is parallel offset from the axis of symmetry of the inlet facing coated wall of the stator parallel to the axis of symmetry of the stator is.
  • This embodiment allows the circumferential removal of the required space for the free rotation of the rotor in the stator space, whereby the offset between the axis of symmetry of the stator and the axis of symmetry of the inlet lining coated wall of the stator can be compensated.
  • the blades of the rotor contain an aluminum-based alloy or iron-based or cobalt-based or nickel-based alloy
  • the stator comprises an aluminum-based alloy or cast steel
  • the blades are exposed to high complex thermal-mechanical stresses.
  • high temperatures and aggressive ambient media promote oxidation and corrosion processes on the blades and the stator housing of the turbomachine. Therefore, in this connection, high temperature resistant and creep resistant iron base or cobalt base or nickel based alloys for the blades of a turbine wheel are preferred used in turbomachinery.
  • the blades for compressors may be made of aluminum-based or iron-based alloys.
  • the turbine and / or compressor blades are made of composite materials on a metallic basis.
  • cast steel is preferably used in the region of the turbine due to the high thermal stresses. By sucking and compressing the cold combustion air, an aluminum-based alloy can be used for the compressor housing due to the thermal stress.
  • the inlet lining on the wall of the stator contains AlSi12 or NiCrAl.
  • This inlet lining has the advantage that it has a cut surface with essentially small grooves (grooving) after the graining process and ensures a minimum gap size between rotating blade tips and the rigid wall of the stator of the turbomachine.
  • the coating of the wall of the stator on the compressor side with the inlet lining of AlSi12 and a filler has the advantage that the coating material has an adapted to the base material of the stator housing thermal expansion behavior.
  • the filler contained in the AlSi12 layer burns out at elevated temperatures, increasing the porosity of the inlet lining.
  • the inlet lining made of AlSi12 is expansion-tolerant and has good adhesion to the base material of the stator housing.
  • the inlet lining made of NiCrAl Due to the high temperature resistance of the inlet lining made of NiCrAl, it can be used both as a coating material for components of the turbine subjected to high temperatures as well as in the thermally less stressed compressor side can be used.
  • the NiCrAl inlet lining contains a filler in accordance with the inlet lining of the compressor side. The inlet lining on the compressor and on the turbine side allows high efficiency and reduced fuel consumption.
  • Another object of the present invention relates to a method for adjusting the stator and rotor of a turbomachine, in which on the wall of the stator an inlet lining is applied and this inlet lining is at least partially removed by the rotor, wherein the rotor is rotated about an axis of rotation parallel offset rotated about the symmetry axis of the stator.
  • An advantage of the method according to the invention is that manufacturing tolerances such as e.g. the size, shape and location of the wall of the stator and / or the internal diameter of the inlet facing coated wall of the stator have a less critical effect on the gap size between blade tips and stator housing.
  • This allows a simple adaptation of the stator and rotor of the turbomachine regardless of whether the axis of symmetry of the rotor coincides with that of the stator or offset parallel thereto.
  • the method according to the invention makes possible an optimum alignment of the rotating rotor with the wall of the stator coated with inlet lining.
  • stator and rotor adjustment process allows the blade mass to be minimized by eliminating the need for scuffing on the blade tips.
  • a reduced mass of the vanes reduces the moment of inertia of the rotor so that the variable load dynamic response of the rotor is improved and overall the dynamic mass forces acting on the blades during operation can be reduced.
  • the rotor is introduced in rotation into the stator.
  • This refinement has the advantage that the rotor rotating around the rotation axis removes the inlet lining uniformly on the rotationally symmetrical surface of the wall such that only the required installation space is cleared of the rotating rotor and the tolerances within the turbomachine are compensated.
  • By removing the inlet lining of the wall over the entire circumference sets a minimum gap size between blade tips and stator.
  • the surface of the abraded inlet lining appears to be slightly rough, so that a profiling of the inlet lining can be achieved without costly preparation and finishing of the coating surface of the inlet lining after the coating process, without costly reworking of the blade tips of the rotor and without expensive Mating the interlocking components of the turbomachine make.
  • the production or production of this turbomachine proves to be very efficient and economical.
  • the rotor can be reversely introduced into the stator. It reversing means that the rotor is first driven over a path length of 1 to 2 mm rotating in the stator and thereby removes material of the inlet lining, then rotated back about 1 to 2 mm, whereby the abraded from the inlet lining and often at least partially attached to the blade tips of the rotor Material can easily peel off. Thereafter, the rotor is retracted again over the path length of 1 to 2 mm plus another 1 to 2 mm rotating in the stator and then extended again. This change between extension and retraction is repeated until the rotor has worn the inlet lining to the desired thickness at the desired depth of the stator.
  • This embodiment has the advantage that, on the one hand, the rotor blades experience a stress reduced in the axial direction and, on the other hand, the gap size is minimized due to the lower blade stresses and the rotor blade deformation thus reduced. In addition, a groove formation is reduced on the inlet lining.
  • FIG. 1 is not to scale an exemplary embodiment of the turbomachine 1 according to the invention in particular the compressor side of an exhaust gas turbocharger with a stator 2 and a rotor 4 shown.
  • the stator 2 has a wall 3, which is internally coated with an inlet lining 6.
  • the rotor 4 is introduced as a compressor wheel with blades 5.
  • the positioning of the rotor 4 in the stator 2 by means of a device not shown here for parallel displacement in the displacement direction 11 and rotation of the rotor 4 about the symmetry axis of the stator second
  • the device for parallel displacement and rotation of the axis of rotation of the rotor 4 consists of a modified commercially available slide bearing.
  • the slide bearing has a rotor which rotates in a housing coated with a bearing layer inside. Between bearing layer and rotor is a 200 micron wide annular gap, the so-called. Lager Kunststoff, which is filled with oil. The oil is removed except for a adhering to the bearing layer minimum amount, and thereby the rotor and with it its axis of rotation due to the centripetal force occurring during its rotation is offset parallel to the axis of symmetry of the housing. The amount of dislocation corresponds to the amount of extracted oil.
  • the rotor 4 is mounted axially symmetrically on the rotor and the modified sliding bearing is positioned axially symmetrically to the stator 2. Thereafter, the rotor, respectively rotor, is set in rotation and carries a part of the inlet lining 6 from. Finally, the rotor 4 can be re-centered by refilling the bearing air of the sliding bearing.
  • This positioning of the rotor 4 in the stator 2 with the aid of the device described is suitable for selected material pairings on rotationally symmetrical surfaces.
  • high-temperature materials are used on the hot turbine side of the exhaust gas turbocharger.
  • the rotor blades of the rotor are made of a Ni-base alloy and the stator of cast steel.
  • the wall of the stator coated with inlet lining on the turbine side is coated with NiCrAl and polyester as filler.
  • the rotor 4 is rotatably introduced into the stator 2 of the compressor side of the exhaust gas turbocharger, which is internally coated with the inlet lining 6.
  • the inlet lining 6 made of AlSi12 is at least partially removed during the positioning in such a way that the rotor 4 is rotated about a rotation axis which rotates offset in a parallel manner about the axis of the stator 2.
  • the invention is not limited to the described example of an exhaust gas turbocharger, but rather can be extended to stationary gas turbines and engines. Furthermore, there is the possibility that the inlet lining on the hot gas side contains NiCrAlY with filler or, for example, ceramic or another high-temperature sealing material.

Abstract

L'invention concerne une turbomachine (1) comprenant : un stator (2) pourvu d'un revêtement d'admission (6) interne ; un rotor (4) qui est disposé dans le stator (2). Cette turbomachine est caractérisée en ce qu'elle comporte en outre un dispositif destiné à décaler de manière parallèle et à faire tourner l'axe de rotation du rotor (10) autour de l'axe de symétrie du stator (2). Ce dispositif permet de réduire la taille de l'interstice entre le stator (2) et le rotor et, par conséquent, d'accroître la rentabilité de la turbomachine (1).

Claims (5)

  1. Turbomachine (1), présentant :
    - un stator (2),
    revêtu à l'intérieur avec un revêtement d'entrée (6),
    - un rotor (4) à l'intérieur du stator (2),
    caractérisée en ce qu'elle présente en outre :
    - un dispositif pour déplacer parallèlement et faire tourner l'axe de rotation du rotor (10) autour de l'axe de symétrie du stator (2).
  2. Turbomachine (1) selon la revendication 1,
    caractérisée en ce que
    les aubes mobiles du rotor (5) contiennent un alliage à base d'aluminium ou un alliage à base de fer ou de cobalt ou de nickel, et le stator (2) contient un alliage à base d'aluminium ou de fonte d'acier.
  3. Turbomachine (1) selon l'une quelconque des revendications précédentes,
    caractérisée en ce que le revêtement d'entrée contient du AlSi12 ou du NiCrAl.
  4. Procédé pour l'adaptation d'un stator (2) et d'un rotor (4) d'une turbomachine (1), dans lequel un revêtement d'entrée (6) est appliqué sur le stator (2) et ce revêtement d'entrée (6) est enlevé au moins en partie par le rotor (4),
    caractérisé en ce que le rotor (4) tourne autour d'un axe de rotation qui tourne de manière décalée parallèlement autour de l'axe de symétrie du stator (2).
  5. Procédé selon la revendication 4,
    caractérisé en ce que le rotor (4) est introduit en tournant dans le stator (2).
EP04765196A 2003-10-13 2004-09-15 Turbomachine et procede pour adapter le stator et le rotor d'une turbomachine Expired - Fee Related EP1721063B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10347524A DE10347524A1 (de) 2003-10-13 2003-10-13 Strömungsmaschine und Verfahren zur Anpassung von Stator und Rotor einer Strömungsmaschine
PCT/EP2004/010282 WO2005038199A1 (fr) 2003-10-13 2004-09-15 Turbomachine et procede pour adapter le stator et le rotor d'une turbomachine

Publications (2)

Publication Number Publication Date
EP1721063A1 EP1721063A1 (fr) 2006-11-15
EP1721063B1 true EP1721063B1 (fr) 2009-03-11

Family

ID=33521596

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04765196A Expired - Fee Related EP1721063B1 (fr) 2003-10-13 2004-09-15 Turbomachine et procede pour adapter le stator et le rotor d'une turbomachine

Country Status (5)

Country Link
US (1) US7850416B2 (fr)
EP (1) EP1721063B1 (fr)
JP (1) JP4475430B2 (fr)
DE (2) DE10347524A1 (fr)
WO (1) WO2005038199A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004042258B3 (de) * 2004-08-30 2006-01-19 Daimlerchrysler Ag Verfahren zur Herstellung eines Konturspalts sowie Strömungsmaschine mit einem Konturspalt
DE102004056179A1 (de) * 2004-11-20 2006-05-24 Borgwarner Inc. Powertrain Technical Center, Auburn Hills Verfahren zur Herstellung eines Verdichtergehäuses
DE102008057878A1 (de) * 2008-11-18 2010-05-20 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
JP5776209B2 (ja) * 2011-02-16 2015-09-09 トヨタ自動車株式会社 回転機器

Family Cites Families (18)

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US2939626A (en) * 1957-12-27 1960-06-07 Laval Steam Turbine Co Turbo-compressor
US3771927A (en) * 1972-03-15 1973-11-13 Purex Corp Impeller running clearance adjustment device
US4291089A (en) * 1979-11-06 1981-09-22 Sherritt Gordon Mines Limited Composite powders sprayable to form abradable seal coatings
US4374173A (en) * 1979-11-06 1983-02-15 Sherritt Gordon Mines Limited Composite powders sprayable to form abradable seal coatings
US4867639A (en) * 1987-09-22 1989-09-19 Allied-Signal Inc. Abradable shroud coating
US5185217A (en) * 1989-09-08 1993-02-09 Toyota Jidosha Kabushiki Kaisha Relatively displacing apparatus
US5196471A (en) * 1990-11-19 1993-03-23 Sulzer Plasma Technik, Inc. Thermal spray powders for abradable coatings, abradable coatings containing solid lubricants and methods of fabricating abradable coatings
US5530050A (en) * 1994-04-06 1996-06-25 Sulzer Plasma Technik, Inc. Thermal spray abradable powder for very high temperature applications
US5658125A (en) * 1995-02-28 1997-08-19 Allison Engine Company, Inc. Magnetic bearings as actuation for active compressor stability control
JP3294491B2 (ja) * 1995-12-20 2002-06-24 株式会社日立製作所 内燃機関の過給機
US5951892A (en) * 1996-12-10 1999-09-14 Chromalloy Gas Turbine Corporation Method of making an abradable seal by laser cutting
WO1999028598A1 (fr) * 1997-12-02 1999-06-10 Siemens Aktiengesellschaft Turbomachine et procede pour ajuster la largeur d'une fente radiale
US6234749B1 (en) * 1998-08-21 2001-05-22 Ishikawajima-Harima Heavy Industries Co., Ltd. Centrifugal compressor
US6290455B1 (en) * 1999-12-03 2001-09-18 General Electric Company Contoured hardwall containment
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
US6547522B2 (en) * 2001-06-18 2003-04-15 General Electric Company Spring-backed abradable seal for turbomachinery
JP2003148103A (ja) 2001-11-09 2003-05-21 Mitsubishi Heavy Ind Ltd タービンおよびその製造方法
US6619913B2 (en) * 2002-02-15 2003-09-16 General Electric Company Fan casing acoustic treatment

Also Published As

Publication number Publication date
DE10347524A1 (de) 2005-01-13
US20070212216A1 (en) 2007-09-13
DE502004009165D1 (de) 2009-04-23
US7850416B2 (en) 2010-12-14
EP1721063A1 (fr) 2006-11-15
JP2007508489A (ja) 2007-04-05
WO2005038199A1 (fr) 2005-04-28
JP4475430B2 (ja) 2010-06-09

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