EP1524411A1 - Procédé pour mesurer et minimiser la fente entre une aube (abrasive) et le carter d'une turbine - Google Patents

Procédé pour mesurer et minimiser la fente entre une aube (abrasive) et le carter d'une turbine Download PDF

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Publication number
EP1524411A1
EP1524411A1 EP03023207A EP03023207A EP1524411A1 EP 1524411 A1 EP1524411 A1 EP 1524411A1 EP 03023207 A EP03023207 A EP 03023207A EP 03023207 A EP03023207 A EP 03023207A EP 1524411 A1 EP1524411 A1 EP 1524411A1
Authority
EP
European Patent Office
Prior art keywords
rotor
housing
electrical
turbine
gap
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
EP03023207A
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German (de)
English (en)
Other versions
EP1524411B1 (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
Original Assignee
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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    • 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 minimization the gap between a rotor and a housing of a Turbine according to the preamble of claim 1 and a Turbine according to the preamble of claim 7 and a Method for determining the wear behavior of a Rotor of a rotor according to claim 14.
  • a rotor rotates with at least one disc and several blades within a housing. Between the Blade end and the housing is a gap.
  • Procedures for displacement of rotor and rotor are from the DE 42 23 495 and WO 00/28190 known.
  • the gap should be minimal between the blade end and housing.
  • the object is achieved by a method according to claim 1, by making the runner and housing part of an electrical circuit are, so with the finding of an electric Contact a mechanical contact is determined.
  • the object is achieved by a turbine according to claim 7, by making the runner and housing part of an electrical circuit are.
  • 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 one Partial longitudinal section.
  • the gas turbine 100 has inside a to a Rotation axis 102 (axial direction) rotatably mounted rotor 103rd on, 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 coaxial arranged burners 107, a turbine 108 and the Exhaust housing 109.
  • the annular combustion chamber 106 communicates with an example annular hot gas duct 111.
  • Each turbine stage 112 is formed of two blade rings.
  • a working medium 113 follows in the hot gas channel 111 a guide vane 115 one of blades 120th formed series 125.
  • the vanes 130 are attached to the stator 143, whereas the blades 120 of a series 125 by a turbine disk 133 are mounted on the rotor 103.
  • On the rotor 103 is coupled to a generator or a Work machine (not shown).
  • the gas turbine 100 During operation of the gas turbine 100 is from the compressor 105 sucked through the intake housing 104 air 135 and compacted. The at the turbine end of the compressor 105th provided compressed air is the burners 107th guided and mixed there with a fuel. The mixture is then to form the working medium 113 in the Combustion chamber 110 burned. From there it flows Working fluid 113 along the hot gas passage 111 past the Vanes 130 and the blades 120. To the Blades 120 relaxes the working fluid 113th momentum transferring, so that the blades 120 the rotor 103 drive and this the coupled to him Working machine.
  • the vanes 130 and Blades 120 of the flow medium of the working medium 113 seen first turbine stage 112 will be in addition to the Annular combustion chamber 106 lining heat shield stones on most thermally loaded. To the ruling there Temperatures are to be withstood by means of a Coolant cooled.
  • the vane 130 has an inner housing 138 of the Turbine 108 facing Leitschaufelfuß (not here shown) and a Leitschaufelfuß opposite Guide vane head on.
  • the vane head is the rotor 103 facing and on a mounting ring 140 of the stator 143rd established.
  • FIG. 2 shows schematically an electrical circuit between a rotor 120 and a housing 138.
  • 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 electrical resistance changes.
  • 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) by an axial displacement of the rotor 120 or the housing 138, the gap d is reduced or increased.
  • FIG. 3 shows a further exemplary embodiment of a turbine 100 embodied according to the invention, with which the method according to the invention can also be carried out.
  • the conicity of the rotor tip of the rotor 120 and the housing 138 is not shown here.
  • the turbine blade 120 and housing 138 are typically made of metallic material so that they can conduct electrical current. Often, however, 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 provides a electrical contact surface 66 is and is for example triangular or conical and can by the Contact with the housing 138 to be worn.
  • 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 separately formed electrical Contact surfaces 66 have, for example, a high electrical Conductivity and / or high wear resistance respectively.
  • the turbine blade 120 may blade tips 87 after The prior art, which is responsible for wear are designed (abradables).
  • the electrical resistance R is plotted via an axial displacement of the guide blade 120 relative to the housing 138.
  • the electrical resistance R (or capacitance) represents a certain gap d between the housing 138 and the turbine blade 120.
  • the axial displacement is, for example, hydraulically by displacement of the rotor 103 with the blades 120 in the axial direction 102. Due to the conicity of the rotor tip and the housing 138 (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 may be determined thereby, 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 results in a curve as shown in Figure 6.
  • 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 per se between the blade tip 87 and the metallic core 72 of the turbine blade 120. 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.

Landscapes

  • 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)
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 true EP1524411A1 (fr) 2005-04-20
EP1524411B1 EP1524411B1 (fr) 2011-07-20

Family

ID=34354444

Family Applications (1)

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

Country Status (2)

Country Link
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
DE102017207240A1 (de) 2017-04-28 2018-10-31 Siemens Aktiengesellschaft Anstreifdetektionsverfahren

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
DE102012213016A1 (de) 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse
US11187247B1 (en) 2021-05-20 2021-11-30 Florida Turbine Technologies, Inc. Gas turbine engine with active clearance control

Citations (7)

* 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
US3775680A (en) * 1971-02-22 1973-11-27 Computas As Device for the detection of wear
GB2063477A (en) * 1979-11-14 1981-06-03 Plessey Co Ltd Measuring Clearance Gap Between Turbine Blades and Surrounding Duct
US4804905A (en) * 1984-09-11 1989-02-14 Mtu Of Postfach Capacitive measuring system for measuring the distance between two relatively movable parts
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
US20030215323A1 (en) * 2002-05-14 2003-11-20 Prinz Friedrich B. Micro gas turbine engine with active tip clearance control

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP1131537B1 (fr) 1998-11-11 2004-10-06 Siemens Aktiengesellschaft Procede de fonctionnement d'une turbomachine

Patent Citations (7)

* 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
US3775680A (en) * 1971-02-22 1973-11-27 Computas As Device for the detection of wear
GB2063477A (en) * 1979-11-14 1981-06-03 Plessey Co Ltd Measuring Clearance Gap Between Turbine Blades and Surrounding Duct
US4804905A (en) * 1984-09-11 1989-02-14 Mtu Of Postfach Capacitive measuring system for measuring the distance between two relatively movable parts
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
US20030215323A1 (en) * 2002-05-14 2003-11-20 Prinz Friedrich B. 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
DE102017207240A1 (de) 2017-04-28 2018-10-31 Siemens Aktiengesellschaft Anstreifdetektionsverfahren
WO2018197086A1 (fr) 2017-04-28 2018-11-01 Siemens Aktiengesellschaft Procédé de détection d'effleurement

Also Published As

Publication number Publication date
EP1524411B1 (fr) 2011-07-20
US20050079048A1 (en) 2005-04-14
US7018165B2 (en) 2006-03-28

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