EP1524411B1 - Turbine et procédé pour minimiser la fente entre une aube et le carter d'une turbine - Google Patents

Turbine et procédé pour minimiser la fente entre une aube et le carter d'une turbine Download PDF

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Publication number
EP1524411B1
EP1524411B1 EP03023207A EP03023207A EP1524411B1 EP 1524411 B1 EP1524411 B1 EP 1524411B1 EP 03023207 A EP03023207 A EP 03023207A EP 03023207 A EP03023207 A EP 03023207A EP 1524411 B1 EP1524411 B1 EP 1524411B1
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EP
European Patent Office
Prior art keywords
casing
turbine
moving blade
gap
housing
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 - Lifetime
Application number
EP03023207A
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German (de)
English (en)
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EP1524411A1 (fr
Inventor
Mirko Milazar
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.)
Siemens AG
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Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP03023207A priority Critical patent/EP1524411B1/fr
Priority to US10/962,934 priority patent/US7018165B2/en
Publication of EP1524411A1 publication Critical patent/EP1524411A1/fr
Application granted granted Critical
Publication of EP1524411B1 publication Critical patent/EP1524411B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D11/14—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position

Definitions

  • the invention relates to a method for minimizing the gap between a blade and a housing of a turbine according to the preamble of claim 1 and a turbine according to the preamble of claim 5.
  • a rotor rotates with at least one disc and a plurality of blades within a housing. There is a gap between the blade end and the housing.
  • Procedures for displacement of rotor and rotor are from the DE 42 23 495 and WO 00/28190 known.
  • the gap between the blade end and housing should be minimal.
  • Methods for gap minimization are from the DE 39 10 319 C2 and the DE 39 01 167 A1 known.
  • the object is achieved by a method according to claim 1, wherein the rotor and the housing are part of an electric circuit, so that a mechanical contact is determined by the detection of an electrical contact.
  • the object is achieved by a turbine according to claim 7, wherein the rotor and the housing are part of an electric circuit.
  • the object is achieved by a method according to claim 14, wherein the rotor and the housing are part of an electric circuit, so that a mechanical contact is determined by the detection of an electrical contact.
  • the distance between the blade end and the housing increases. This can be determined by the method according to claim 13, by determining the course of the temporal change in distance.
  • FIG. 1 shows a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
  • a compressor 105 for example a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109.
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • a series 125 formed of rotor blades 120 follows.
  • the vanes 130 are attached to the stator 143, whereas the blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 becomes the burners 107 guided and mixed there with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 2 schematically shows an electrical circuit between a rotor 120 and a housing 138th
  • an electrical connection by means of electrical lines 60 or electromagnetic transmission, for example via the shaft between the turbine blade 120 and the housing 138 produced.
  • a corresponding measuring device 63 voltage, current, resistance or capacitance meter
  • an electrical resistance and / or another electrical parameter can be measured.
  • the electrical resistance between at least one, shown schematically here, turbine blade 120 and the housing 138 can be measured. When there is no contact between the turbine blade 120 and the housing 138, the electrical resistance is very or infinitely high.
  • the measured electrical quantity is thus a measure of the existing size of a gap d between the blade heads and the housing. Due to the conicity of the rotor tip of the rotor 120 and the housing 138 to each other ( Fig. 1 . WO 00/28190 ) is reduced or increased by an axial displacement of the rotor 120 or the housing 138, the gap d.
  • FIG. 3 shows an embodiment of an inventively designed turbine 100, with which the inventive method can be performed.
  • the turbine blade 120 and housing 138 are typically made of metallic material so that they can conduct electrical current.
  • the turbine blade 120 has a ceramic coating, so that an electrical current flow between the turbine blade 120 and the housing 138 would not be possible. In these cases, an electrical path between the housing 138 and the turbine blade 120, in particular the blade tip 87, must be made possible by additional measures.
  • the projection 69 on the turbine blade 120 constitutes an electrical contact surface 66 and is for example triangular or conical and may be worn out by contact with the housing 138.
  • the projection 69 may be provided on one or more turbine blades 120 of one or more turbine stages 112.
  • the at least one projection 69 is, for example, aligned with an electrical contact surface 66 of the opposite housing 138.
  • the housing 138 may have separately formed electrical contact surfaces 66 which have, for example, high electrical conductivity and / or high wear resistance.
  • the turbine blade 120 may include blade tips 87 of the prior art that are designed for wear (abradables).
  • the electrical resistance R applies via an axial displacement of the guide vane 120 relative to the housing 138th
  • the electrical resistance R represents a certain gap d between the housing 138 and the turbine blade 120.
  • the axial displacement takes place, for example, hydraulically by displacement of the rotor 103 with the rotor blades 120 in the axial direction 102. Due to the conicity of the rotor tip and the housing 138 (FIG. Fig. 1 . WO 00/28190 ) the gap d is thereby reduced.
  • the electrical resistance R for example, has a certain value or is infinitely high.
  • an end time can be determined in which a Verissiß Mrs 75 ( Fig. 5 ) is consumed on the turbine blade 120. This is done by determining continuously or discontinuously with time t over which distance x the rotor 103 has been readjusted relative to the housing 138 in order to set a specific minimum gap. This gives a curve like in FIG. 6 shown. This distance x corresponds to a certain layer thickness loss. Since the layer thickness h of the layer 75 is known, it can be determined by means of the entire distance of the readjustment x when the layer 75 is consumed or how thick it still is.
  • FIG. 5 shows a turbine blade 120 of a turbine 100 designed according to the invention.
  • the turbine blade 120 has a metallic substrate 72 which (not shown) has a ceramic coating 75 and / or an outer wear layer 75.
  • the Outer wear layer 75 is, for example, porous and / or ceramic, so that there would be no electrical path between the blade tip 87 and the metallic core 72 of the turbine blade 120 per se. Therefore, at least one continuous electrical path 78 is produced in the wear protection layer 75.
  • the electrical path 78 may be present in one or more turbine blades 120 of one or more rows of blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Procédé de minimisation de l'intervalle ( d ) entre une aube ( 120 ) mobile et un carter ( 138 ) d'une turbine ( 100 ),
    dans lequel l'intervalle ( d ) entre l'aube ( 120 ) mobile et le carter ( 138 ) peut être réglé par déplacement de l'aube ( 120 ) de turbine et du carter ( 138 ) l'un par rapport à l'autre et les aubes ( 120 ) mobiles et le carter ( 138 ) font parti d'un circuit ( 120, 60, 138 ) de courant,
    caractérisé en ce qu'il est prévu sur la pointe ( 87 ) de l'aube au moins une saillie ( 69 ) qui est conductrice de l'électricité, qui est en forme de triangle et qui peut être mise en contact avec une surface ( 66' ) de contact côté carter du circuit ( 120, 60, 138 ) de courant,
    dans lequel la résistance électrique du circuit ( 120, 60, 138 ) de courant est mise à profit comme mesure de la dimension de l'intervalle ( d ) et ainsi pour régler un intervalle ( d ),
    dans lequel une valeur de résistance électrique mesurable signifie qu'un contact électrique est présent au moins en partie entre l'aube ( 120 ) mobile et le carter ( 138 ).
  2. Procédé suivant la revendication 1,
    caractérisé en ce qu'une valeur de résistance électrique infiniment grande signifie qu'il n'y a pas de contact électrique entre l'aube ( 120 ) mobile et le carter ( 138 ).
  3. Procédé suivant la revendication 1,
    caractérisé en ce que l'on applique une tension entre l'aube ( 120 ) mobile et le carter ( 138 ),
    la chute de tension étant mise à profit comme mesure de la dimension de l'intervalle entre l'aube ( 120 ) mobile et le carter ( 138 ).
  4. Procédé suivant la revendication 1, 2 ou 3,
    caractérisé en ce l'aube ( 120 ) mobile peut pour régler la dimension de l'intervalle être déplacée dans une direction ( 102 ) axiale par rapport au carter ( 138 ).
  5. Turbine, notamment turbine à gaz,
    comprenant une aube ( 120 ) mobile et un carter ( 138 ), l'aube ( 120 ) mobile pouvant pour régler la dimension de l'intervalle être déplacée dans une direction ( 102 ) axiale par rapport au carter ( 138 ) et l'aube ( 120 ) mobile et le carter ( 138 ) faisant parti d'un circuit ( 120, 60, 138 ) de courant électrique,
    caractérisé en ce qu'il est prévu sur une pointe ( 87 ) de l'aube au moins une saillie ( 69 ) qui est conductrice de l'électricité, qui est en forme de triangle et qui peut être mise en contact avec une surface ( 66' ) côté carter du circuit ( 120, 60, 138 ) de courant et
    en ce que la résistance électrique peut être déterminée comme représentative de la dimension de l'intervalle ( d ) entre l'aube ( 120 ) mobile et le carter ( 138 ).
  6. Turbine suivant la revendication 5,
    caractérisée en ce qu'au moins une aube ( 120 ) mobile comporte au moins une surface ( 66 ) de contact électrique ménagée séparément.
  7. Turbine suivant la revendication 5 ou 6,
    caractérisée en ce que le carter ( 138 ) a au moins une surface ( 66' ) de contact électrique ménagée séparément.
  8. Turbine suivant la revendication 5, 6 ou 7
    caractérisée en ce la saillie ( 69 ) et/ou l'aube ( 120 ) mobile peut avoir été traitée par abrasion.
EP03023207A 2003-10-13 2003-10-13 Turbine et procédé pour minimiser la fente entre une aube et le carter d'une turbine Expired - Lifetime EP1524411B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP03023207A EP1524411B1 (fr) 2003-10-13 2003-10-13 Turbine et procédé pour minimiser la fente entre une aube et le carter d'une turbine
US10/962,934 US7018165B2 (en) 2003-10-13 2004-10-12 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

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03023207A EP1524411B1 (fr) 2003-10-13 2003-10-13 Turbine et procédé pour minimiser la fente entre une aube et le carter d'une turbine

Publications (2)

Publication Number Publication Date
EP1524411A1 EP1524411A1 (fr) 2005-04-20
EP1524411B1 true EP1524411B1 (fr) 2011-07-20

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US (1) US7018165B2 (fr)
EP (1) EP1524411B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012213016A1 (de) 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
FI123228B (fi) 2010-04-20 2012-12-31 Waertsilae Finland Oy Järjestely akselin aksiaalisen liikkeen havaitsemiseksi
EP2397656A1 (fr) * 2010-06-14 2011-12-21 Siemens Aktiengesellschaft Procédé de réglage de l'espace radial entre les extrémités de pales d'aubes mobiles et une paroi de canal ainsi que dispositif de mesure d'un espace radial d'une turbomachine pouvant à écoulement axial
EP2549059A1 (fr) * 2011-07-21 2013-01-23 Siemens Aktiengesellschaft Procédé destiné au fonctionnement d'une machine rotative
US20130171611A1 (en) * 2012-01-03 2013-07-04 General Electric Company Apparatus for simulating operation of fan blades in a gas turbine
DE102017207240A1 (de) 2017-04-28 2018-10-31 Siemens Aktiengesellschaft Anstreifdetektionsverfahren
US11187247B1 (en) 2021-05-20 2021-11-30 Florida Turbine Technologies, Inc. Gas turbine engine with active clearance control

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1094780A (en) * 1967-05-25 1967-12-13 Prvni Brnenska Strojirna Zd Y Improvements in or relating to protection devices for bladed fluid-flow machines
NO134348C (fr) * 1971-02-22 1976-09-22 Asea Ab
GB2063477A (en) * 1979-11-14 1981-06-03 Plessey Co Ltd Measuring Clearance Gap Between Turbine Blades and Surrounding Duct
DE3433351C1 (de) * 1984-09-11 1986-01-02 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Kapazitives Messsystem zur Messung des Abstandes zwischen zwei relativ zueinander beweglichen Teilen
GB2204693B (en) * 1987-05-14 1991-02-13 Rolls Royce Plc Turbomachine tip clearance sensor
US5012420A (en) 1988-03-31 1991-04-30 General Electric Company Active clearance control for gas turbine engine
DE3901167A1 (de) 1989-01-17 1990-07-26 Klein Schanzlin & Becker Ag Spaltminimierung
DE4223495A1 (de) 1992-07-17 1994-01-20 Asea Brown Boveri Gasturbine
DE4315125A1 (de) * 1993-05-07 1994-11-10 Daimler Benz Ag Verfahren und Anordnung zur Bestimmung des Spitzenspiels von Turbinenrotorschaufeln
WO1999028598A1 (fr) * 1997-12-02 1999-06-10 Siemens Aktiengesellschaft Turbomachine et procede pour ajuster la largeur d'une fente radiale
EP1131537B1 (fr) 1998-11-11 2004-10-06 Siemens Aktiengesellschaft Procede de fonctionnement d'une turbomachine
US6692222B2 (en) * 2002-05-14 2004-02-17 The Board Of Trustees Of The Leland Stanford Junior University Micro gas turbine engine with active tip clearance control

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012213016A1 (de) 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse
WO2014016153A1 (fr) 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Procédé pour réduire au minimum une fente entre un rotor et un carter

Also Published As

Publication number Publication date
US20050079048A1 (en) 2005-04-14
US7018165B2 (en) 2006-03-28
EP1524411A1 (fr) 2005-04-20

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