WO1999028598A1 - Turbomachine et procede pour ajuster la largeur d'une fente radiale - Google Patents

Turbomachine et procede pour ajuster la largeur d'une fente radiale Download PDF

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Publication number
WO1999028598A1
WO1999028598A1 PCT/DE1997/002811 DE9702811W WO9928598A1 WO 1999028598 A1 WO1999028598 A1 WO 1999028598A1 DE 9702811 W DE9702811 W DE 9702811W WO 9928598 A1 WO9928598 A1 WO 9928598A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
turbomachine
gap width
blades
housing
Prior art date
Application number
PCT/DE1997/002811
Other languages
German (de)
English (en)
Inventor
Jürgen HERMELER
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/DE1997/002811 priority Critical patent/WO1999028598A1/fr
Publication of WO1999028598A1 publication Critical patent/WO1999028598A1/fr

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
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters

Definitions

  • the invention relates to a turbomachine with an at least partially conical housing and a rotor, the rotor having a row of rotor blades comprising a plurality of rotor blades, each rotor blade having a conical blade tip, which blade tip is spaced from the housing over a respective radial gap of a respective gap width.
  • the invention further relates to a method for setting a gap width of a radial gap between an at least partially conical housing and conical blade tips of a rotor blade row of a turbomachine.
  • a hot gas which is conducted in a flow in the housing strikes the rotor blades of a row of rotor blades of a rotor located in the housing, the rotor being set in rotation.
  • the blade tips of the rotor blades must be spaced from the housing via a respective radial gap, even at an operating temperature. A part of the flows through the radial gap
  • gap loss Hot gas without affecting the blades and contributing to the rotation of the rotor. This is called gap loss.
  • the housing When operating a gas turbine, a hot gas flows through the housing in one direction of flow. The pressure of the hot gas decreases, so that it expands.
  • the housing therefore has a contour which is at least partially conical and has a cross section which widens as a result in the flow direction.
  • the blade tips are also conical.
  • the conical housing can have an angle of inclination with respect to a machine axis that is approximately 30 °.
  • Turbo machine conical and with a cover band.
  • the cover band is adjustable so that the gap width of the radial gap can be changed.
  • the shroud can be displaced essentially in the axial direction even during operation of the turbomachine, so that the gap width can also be varied during operation.
  • the object of the invention is to provide a turbomachine in which the gap width of a radial gap between a housing and a blade tip of a moving blade can be adjusted. Another object is to specify a method with which the gap width of the radial gap is set.
  • the object directed to a turbo machine is achieved by a turbomachine according to the preamble of claim 1, wherein the rotor has a spacer for axial positioning of the blade row relative to the housing, so that the gap width at an operating temperature m is a predetermined setpoint range.
  • a disk runner is a runner that is formed from a plurality of runner disks.
  • the rotor disks are held together by at least one tie rod.
  • the rotor disks each have an outer circumference, on which the rotor blades are attached and form a row of rotor blades.
  • the spacing means is preferably also disc-shaped and integrated in the disc rotor so that adjacent rotor discs are spaced apart from one another.
  • the spacer is preferably arranged between two rotor disks, each with a row of rotor blades, and has a width that determines the distance.
  • the distance is changed, as a result of which a respective axial position of a rotor disk can be changed.
  • the gap width of the radial gap can be adjusted by changing the axial position of the rotor disk and thus the row of rotor blades.
  • the distance between two rotor disks is selected so that the gap width of the radial gap at the operating temperature is in the specified setpoint range.
  • the spacer is preferably ring-shaped, in particular as a spacer ring.
  • the rotor has a plurality of rows of blades, the spacer being arranged between two adjacent rows of blades. In this way, the axial position of one of the two rows of blades can be changed and the gap width of the radial gap can be set for this one row of blades.
  • the spacer is preferably interchangeable. This is particularly the case with a rotor that is designed as a disc rotor. As a result, the gap width can be changed simply by mounting different spacing means, for example with different dimensions.
  • the object directed to a method for setting a gap width of a radial gap is achieved by a method according to the preamble of claim 6, in which the axial position of the rotor blade row on the rotor is changed by a distance.
  • a first gap width of the radial gap is preferably determined and / or set when the turbomachine is at a normal temperature.
  • a second gap width of the radial gap is determined for the turbomachine that is at an operating temperature.
  • the distance for changing the axial position is determined taking into account the first gap width, the second gap width and a predefined setpoint range. L OJ t to P 1 P>
  • the single figure shows schematically and partially not to scale, showing the structural and functional features used for the explanation, a longitudinal section through a conical housing of a turbomachine.
  • a longitudinal section of a turbomachine 1 with a conical housing 5 and a rotor 9 is shown in sections.
  • the housing 5 has the angle of inclination ⁇ with respect to a main axis (not shown).
  • the rotor 9, which extends along the main axis, is designed as a disk rotor and has the rotor disks 60 and 61.
  • the rotor disks 60 and 61 are designed as rows of moving blades. In the following, they are also referred to alternatively as rotor blade rows 60 and 61.
  • the blade rows 60 and 61 each comprise a plurality of blades 70 and 71 with conical blade tips 40 and 41, respectively.
  • the blade tips 40, 41 are each spaced apart from the housing 5 by a radial gap of a gap width S1 or S2.
  • the rotor has a spacer 8, which is attached between the two rows of blades 60 and 61.
  • the spacing means 8 has a width L with which the rotor blade rows 60 and 61 are spaced apart from one another. Furthermore, the spacer 8 is preferably designed as a spacer ring.
  • the axial position of the rotor blade row 61 can be changed and the gap width S2 can thus be set such that it lies in a predetermined target value range.
  • the following procedure is used to set the gap width S2: At a normal temperature, which can possibly deviate from an ambient temperature, a first width L des Distance means selected and thus set the gap width S2 to a first gap width S21.
  • the turbomachine is placed in a correspondingly selected hot state so that the thermal expansion of the housing 5 and the rotor blade 71 reach a stationary final state, for which a second gap width S22 is measured, for example by means of a stylus measurement.
  • a change in the width L by a distance .DELTA.L can be determined from the determined gap widths S21 and S22 and a predetermined gap width which lies in a target value range.
  • the distance .DELTA.L is determined in such a way that, after a change in the axial position of the blade row 61 by the distance .DELTA.L, the gap width S2 is set at a desired operating temperature such that it lies within the predefined setpoint range. This can be both a reduction and a
  • Increasing the width L by a distance ⁇ L may be necessary. This is indicated with the corresponding signs (-) and (+). It is particularly advantageous that the spacer 8 is easy to install and remove.
  • the rotor 9 can be dismantled at a normal or ambient temperature and a spacer ring with a predetermined width L can be used.

Landscapes

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

Abstract

L'invention concerne une turbomachine dont la taille (S) de la fente radiale (2) est réglable, ainsi qu'un procédé permettant d'ajuster la taille (S) voulue de la fente radiale entre le carter (5) et une série d'aubes mobiles (3) d'une turbomachine (1) dont la température est très élevée, Les pointes des aubes (4) de la série d'aubes mobiles (3) et au moins une partie du carter (5) s'étendant de manière conique. Ce procédé comprend les étapes suivantes: ajuster une taille (S) prédéterminée de la fente radiale (2) lorsque la turbomachine (1) est froide; mesurer la taille (S) de la fente radiale (2) une fois que la température de la turbomachine (1) est très élevée; calculer une distance différentielle (ΔL) pour une position axiale de la série d'aubes mobiles (3) par rapport au boîtier (5), afin d'atteindre une taille (S) voulue de la fente radiale (2) lorsque la turbomachine (1) est chaude; et enfin, modifier la taille (S) de la fente radiale (2), par modification de la position axiale de la série d'aubes mobiles (3) conformément à la distance différentielle (ΔL) calculée.
PCT/DE1997/002811 1997-12-02 1997-12-02 Turbomachine et procede pour ajuster la largeur d'une fente radiale WO1999028598A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/DE1997/002811 WO1999028598A1 (fr) 1997-12-02 1997-12-02 Turbomachine et procede pour ajuster la largeur d'une fente radiale

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/DE1997/002811 WO1999028598A1 (fr) 1997-12-02 1997-12-02 Turbomachine et procede pour ajuster la largeur d'une fente radiale

Publications (1)

Publication Number Publication Date
WO1999028598A1 true WO1999028598A1 (fr) 1999-06-10

Family

ID=6918561

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE1997/002811 WO1999028598A1 (fr) 1997-12-02 1997-12-02 Turbomachine et procede pour ajuster la largeur d'une fente radiale

Country Status (1)

Country Link
WO (1) WO1999028598A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10347524A1 (de) * 2003-10-13 2005-01-13 Daimlerchrysler Ag Strömungsmaschine und Verfahren zur Anpassung von Stator und Rotor einer Strömungsmaschine
EP1524411A1 (fr) * 2003-10-13 2005-04-20 Siemens Aktiengesellschaft Procédé pour mesurer et minimiser la fente entre une aube (abrasive) et le carter d'une turbine
JP2005337248A (ja) * 2004-05-27 2005-12-08 Rolls Royce Plc 間隙形成構造体

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1823310A (en) * 1929-05-23 1931-09-15 Westinghouse Electric & Mfg Co Elastic fluid turbine
DE1178253B (de) 1962-03-03 1964-09-17 Maschf Augsburg Nuernberg Ag Axial-durchstroemte Kreiselradmaschine mit einstellbarem Deckband
DE1291560B (de) 1963-09-20 1969-03-27 Licentia Gmbh Abdeckring bei schraegem Laufschaufelradialspalt einer Axialturbomaschine, insbesondere -gasturbine
DE2165528A1 (de) * 1971-12-30 1973-07-12 Kloeckner Humboldt Deutz Ag Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine
WO1993020335A1 (fr) * 1992-04-01 1993-10-14 Abb Carbon Ab Procede et dispositif pour une machine tournante
US5263816A (en) * 1991-09-03 1993-11-23 General Motors Corporation Turbomachine with active tip clearance control
FR2722836A1 (fr) * 1994-07-20 1996-01-26 Snecma Turbomachine munie de moyens d'ajustement du jeu radial entre rotor e stator
DE19625865A1 (de) * 1996-06-27 1998-01-02 Siemens Ag Einstellbare Größe eines Radialspaltes einer Turbomaschine und Verfahren dazu

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1823310A (en) * 1929-05-23 1931-09-15 Westinghouse Electric & Mfg Co Elastic fluid turbine
DE1178253B (de) 1962-03-03 1964-09-17 Maschf Augsburg Nuernberg Ag Axial-durchstroemte Kreiselradmaschine mit einstellbarem Deckband
DE1291560B (de) 1963-09-20 1969-03-27 Licentia Gmbh Abdeckring bei schraegem Laufschaufelradialspalt einer Axialturbomaschine, insbesondere -gasturbine
DE2165528A1 (de) * 1971-12-30 1973-07-12 Kloeckner Humboldt Deutz Ag Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine
US5263816A (en) * 1991-09-03 1993-11-23 General Motors Corporation Turbomachine with active tip clearance control
WO1993020335A1 (fr) * 1992-04-01 1993-10-14 Abb Carbon Ab Procede et dispositif pour une machine tournante
FR2722836A1 (fr) * 1994-07-20 1996-01-26 Snecma Turbomachine munie de moyens d'ajustement du jeu radial entre rotor e stator
DE19625865A1 (de) * 1996-06-27 1998-01-02 Siemens Ag Einstellbare Größe eines Radialspaltes einer Turbomaschine und Verfahren dazu

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10347524A1 (de) * 2003-10-13 2005-01-13 Daimlerchrysler Ag Strömungsmaschine und Verfahren zur Anpassung von Stator und Rotor einer Strömungsmaschine
EP1524411A1 (fr) * 2003-10-13 2005-04-20 Siemens Aktiengesellschaft Procédé pour mesurer et minimiser la fente entre une aube (abrasive) et le carter d'une turbine
US7018165B2 (en) 2003-10-13 2006-03-28 Siemens Aktiengesellschaft Method of minimizing the gap between a rotating turbine blade and a casing of a turbine, a turbine, and a method of determining the wear behavior of a wheel of a rotor
US7850416B2 (en) 2003-10-13 2010-12-14 Daimler Ag Turboengine and method for adjusting the stator and rotor of a turboengine
JP2005337248A (ja) * 2004-05-27 2005-12-08 Rolls Royce Plc 間隙形成構造体
US7246994B2 (en) 2004-05-27 2007-07-24 Rolls-Royce Plc Spacing arrangement

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