EP2994617A1 - Turbine et procédé de détection de frottement - Google Patents

Turbine et procédé de détection de frottement

Info

Publication number
EP2994617A1
EP2994617A1 EP14738405.1A EP14738405A EP2994617A1 EP 2994617 A1 EP2994617 A1 EP 2994617A1 EP 14738405 A EP14738405 A EP 14738405A EP 2994617 A1 EP2994617 A1 EP 2994617A1
Authority
EP
European Patent Office
Prior art keywords
rotor
turbine
housing
frequency
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.)
Withdrawn
Application number
EP14738405.1A
Other languages
German (de)
English (en)
Inventor
Alexander SEROKA
Raoul Costamagna
Uwe Sieber
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
Publication of EP2994617A1 publication Critical patent/EP2994617A1/fr
Withdrawn legal-status Critical Current

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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2260/00—Function
    • F05D2260/83—Testing, e.g. methods, components or tools therefor

Definitions

  • the invention relates to a turbine, especially a gas ⁇ turbine, comprising a rotor, a monitoring system by a gap spaced from the rotor housing and a Whyschallüberwa-. It further relates to a method for squeak detection in a turbine, in particular a gas turbine, comprising a rotor, a spaced-apart by a gap from the rotor housing and a structure-borne noise monitoring system.
  • a turbine is a flow machine, which the internal energy (enthalpy) into a flowing fluid (liquid or gas) into rotational energy and, ultimately, into mechanical energy to drive ⁇ .
  • the fluid stream is removed from a part of its internal energy through the possibility ⁇ lichst irrotational laminar flow around the turbine blades, which turns the rotor blades of the turbine.
  • the turbo is then binenwelle rotated, the useful power is delivered to an implement coupled to the working machine, such as in egg ⁇ NEN generator.
  • Blades and shaft are parts of the movable rotor or rotor of the turbine, which is arranged within a housing.
  • Blades mounted on the axle are mounted on the axle. Blades mounted in a plane each form a paddle wheel or impeller. The blades are slightly curved profiled, similar to an aircraft wing. Before each wheel is usually a stator. These Leitschau ⁇ feln protrude from the housing into the flowing medium and put it in a twist. The swirl generated in the stator (kinetic energy) is used in the following impeller to set the shaft on which the impeller blades are mounted in rotation.
  • the stator and the impeller together are called stages. Often several such stages are connected in series. Since that Stator is stationary, its vanes can be mounted both on the inside of the housing and on the outside of the housing, and thus provide a bearing for the shaft of the impeller. Between the guide blade ends of the rotor and the housing is usually a gap, which serves for example to compensate for the thermal expansion during operation. However, in order to achieve high efficiency, the gap between the blade end and the housing should be minimal, since fluid flows past the rotor blades through the gap and thus does not contribute to the generation of energy.
  • Actuator to influence the gap size typically only a displacement of the rotor by a fixed, predetermined length, z. B. 2.4 or 3.0 mm instead. It is also known to use structure-borne noise monitoring systems in order to dynamically detect a tarnishing of the turbine by means of the detection of the vibrations generated by the rotor rubbing against the housing and thus to optimize the gap by further methods. The previously known systems, however, only allow a principle recognition of a strip. For a further gap ⁇ optimization z. B. also shortly after plant start, if the turbine is not completely warmed through, it would be desirable to be able to localize the rubbing as accurately as possible.
  • the object is achieved according ge ⁇ dissolved by mixing in a first and a second axial region one or more inwardly directed abrading teeth of the housing and one or more outwardly directed An ⁇ grazing edges of the rotor are arranged, and wherein the one or more Adjuster teeth and the or the squinting edges are distributed along the circumference such that a touch each ⁇ wan squealer teeth and squinting edges at a pregiven ⁇ given rotational frequency of the rotor in the first axial region with a different frequency than in the second axial region.
  • the object is achieved by a contact in a first axial region is detected by the structure-borne noise monitoring system when exceeding a limit amplitude of a first, derived from the rotational frequency of the rotor frequency, and at a second from the rotational frequency of the rotor derived and at the same rotational frequency of the rotor to the first frequency different frequency, a contact in a second axial range is detected.
  • the invention is based on the consideration that a technically particularly localization of the AnstMails would be achievable if this would be possible only by the structure-borne noise monitoring ⁇ system, without additional sensors would be necessary.
  • Associable This would require Anstreifereignisse different locations based on the product it creates body vibration be distinguishable, so that a particular structure-borne noise signal a ⁇ be agreed location.
  • An easily distinguishable parameter here is the frequency of the signal. This is dependent on the current rotational frequency, but can be modified by the fact that at the rotor corresponding Anstreifkanten and the housing corresponding Abstzähne positioned who ⁇ the. Depending on the configuration of the edges and teeth results in the soaking a characteristic signal.
  • edges and teeth are arranged such that they produce different frequencies under ⁇ different axial union areas, the rubbing in the axial direction is locatable.
  • a different number of Anstreif ⁇ edge is uniform around the circumference of the rotor angeord- net.
  • An evenly distributed number of squint edges he ⁇ is namely in terms of the method advantageously a body vibration with a frequency which is an integer multiple of the rotational frequency.
  • the squealer teeth are so ver ⁇ shares along the circumference of the housing, that result in different distances between adjacent in the circumferential direction on-scoring teeth.
  • the Zäh ⁇ ne thereby positioned close enough so that there is a rubbing of two teeth, two oscillations of the same frequency are produced whose phase distance is correlated with the spacing of the teeth.
  • a position of the contact in the circumferential direction is then advantageously determined on the basis of a phase shift of two superimposed signals of the same frequency.
  • adjoining squeal teeth in the circumferential direction have a spacing which increases linearly in the circumferential direction.
  • the size of the phase shift is advantageously linked linearly with the angular position of the contact with regard to the method. This allows a particularly simple location of the striping in the circumferential direction.
  • the structure-borne noise monitoring system has a plurality of long of the circumference of distributed vibration sensor.
  • the method may thereby the location of the touch are determined in the circumferential direction is advantageously based on the amplitude ratios of the signals along the order ⁇ fangs distributed vibration sensor.
  • the gap between rotor and housing by means of an adjusting device is adjustable, in particular by displacement of rotor and housing against each other, and the adjusting device is the input side connected to the structure-borne noise monitoring system.
  • a minimum gap (d) is set by means of the described squirt detection method. In this case, the runner is moved until no output signals erzeu ⁇ gender contact is no longer available. That is, the rotor is displaced until the turbine blade blisk contacts the housing. This contact is monitored by means thoroughlyschallü ⁇ monitoring system and the traverse limited thereby. As soon as a first contact indication is registered, the runner is fixed, possibly after a short push-back - just at the border to the contact. The
  • Direction of the shift can be optimized due to the exact location of the stripe.
  • a turbine advantageously has means for carrying out the described method.
  • a power plant advantageously comprises a be ⁇ written turbine.
  • the advantages achieved with the invention consist in particular in that due to the accurately localizable Maiserken ⁇ voltage between the rotor and housing has a still further optimized to minimize the gaps between the rotor and housing with tech- nisch particularly simple means is possible.
  • the An can roam ⁇ in many places in both the axial and circumferential directions during operation of the turbine recognized without internal instrumentation and with few transducers advertising to. Even existing turbines can be retrofitted with appropriate squint edges and teeth.
  • 1 shows a partial longitudinal section through a Gasturbi ⁇ ne.
  • 2 schematically shows a cross section through a first radial region of the gas turbine
  • FIG. 3 schematically shows a cross section through a second radial region of the gas turbine.
  • 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 rotation axis 102 axial direction
  • the annular combustion chamber 106 communicates with an annular hot-gas passage 111, where, for example, form four hinterei ⁇ Nander turbine stages 112 form the turbine 108.
  • Each turbine stage 112 is formed from two blade or vane rings. Seen in the flow direction of a working medium 113, in the hot-gas passage 111 a row of guide vanes 115 formed from rotor blades 120 ⁇ series 125th
  • the guide vanes 130 are fastened to the stator 143, whereas the rotor blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133.
  • the run ⁇ blades 120 thus form components of the rotor or Läu ⁇ fers 103.
  • Coupled to the rotor 103 is a generator or a working machine (not shown).
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the 105 ⁇ be compressed air provided at the turbine end of the compressor is supplied to the burners 107, where it is mixed 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 on the rotor blades 120 in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine connected 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 guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not Darge here provides ⁇ ) and a side opposite the guide-blade root vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • the gas turbine 100 shows a structure-borne sound monitoring system, which is not shown in more detail, which is connected to a plurality of sensors on the rotor 103 and the housing 138, the output signals relative to the borrowing of the turbine 100 sound vibrations.
  • the rotor 103 is axially displaceable along the axis 102. Due to the conicity of the rotor tip of the rotor 103 and the housing 138 to each other is the gap d between the rotor 103, especially the blade ends, and the housing is reduced by a Axi ⁇ alverschiebung of the rotor 103 or the housing 138 or 138 increases.
  • the Axial ⁇ shift is hydraulic.
  • vanes 120 When a first contact has been made, the vanes 120 are fixed or, if the contact is still too strong, they are shifted back until there is no more contact indicated by a corresponding output signal. Then a minimum gap d is set. This ⁇ A position of the minimum gap, during operation, ty- pisch expediently take place after complete heating of the turbine 100th
  • the turbine 100 is provided with respective structural measures are ⁇ tert the erläu in the following FIG. 2 and 3
  • Figures 2 and 3 show a cross section through two radial loading rich of the compressor 105, more specifically in each case by a ring of rotor blades 120 with the surrounding housing 138. Disposed on ⁇ roaming teeth 146 along the circumference on the inside of the housing 138, the radially protrude inside. At the radially outer end of some blades 120 squealer edges 148 are arranged.
  • squealer edges 148 are arranged at a uniform interval along the circumferential direction, ie at an angular interval of ninety degrees each.
  • three Anstreif ⁇ edges are arranged at equal distances along the circumferential direction 148, that is, with an angular distance of each one hundred and twenty degrees.
  • touching abutting edges 148 and abutting teeth 146 in the first region produces a structure-borne sound signal having a frequency which is four times the current rotational frequency of rotor 103
  • touching squealer edges 148 and abutting teeth 146 in the second region produces a structure-borne sound signal with a ner frequency corresponding to three times the current rotational frequency of the rotor 103, arises.
  • squash edges 148 are distributed at other distances in other areas of the compressor.
  • the abrading teeth 146 on the housing 138 are distributed in FIGS. 2 and 3 in the circumferential direction from the uppermost point with a linearly increasing distance. This also makes it possible to localize the rubbing in the circumferential direction, since when rubbed against two squealer teeth 146 two structure-borne sound signals of the same frequency are generated, whose phase shift is different depending on the distance of the squealer teeth 146. Since each distance of adjacent squeal teeth 146 is different, it can be concluded from the magnitude of the phase shift on the circumferential position of the squiggle.
  • the squint edges and teeth 146, 148 have an outer wear layer.
  • the outer wear layer is, for example, porous and / or ceramic, so that even a small contact does not cause permanent damage.
  • the evaluation method in the structure-borne noise monitoring system is designed for a corresponding analysis of the signal, it can resolve frequencies and phase shifts.
  • Data on the structural arrangement of the squealer edges and teeth 146, 148 are stored in the structure-borne noise monitoring system.
  • the structure-borne noise monitoring system has access to the current rotational speed of the rotor 103 on the input side.
  • the structure-borne sound monitoring system is designed for a Peilortung, ie there are several sound sensors distributed along the circumference. By analyzing the magnitude of the amplitudes of the acoustic sensors, the structure-borne noise monitoring system can determine the relative proximity of the rubbing event to the respective acoustic sensor and, in the manner of a bearing, a Localization.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

L'invention concerne une turbine (100), notamment une turbine à gaz, comprenant un rotor (103), une enveloppe (138) espacée du rotor (103) par un interstice (d) et un système de surveillance des bruits de structure, qui doit permettre une localisation d'un frottement du rotor et de l'enveloppe avec une complexité technique aussi réduite que possible. Pour ce faire, une ou plusieurs dents de frottement (146) de l'enveloppe (138), dirigées vers l'intérieur, et une ou plusieurs arêtes de frottement (148) du rotor (103), dirigées vers l'extérieur, sont respectivement disposées dans une première et une deuxième zone axiale. La ou les dents de frottement (146) ainsi que la ou les arêtes de frottement (148) sont distribuées la long du pourtour de telle sorte qu'un contact entre les dents de frottement (146) et les arêtes de frottement (148) respectives à une fréquence de rotation prédéfinie du rotor (103) a lieu dans la première zone axiale à une fréquence différente par rapport à la deuxième zone axiale.
EP14738405.1A 2013-06-26 2014-06-18 Turbine et procédé de détection de frottement Withdrawn EP2994617A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013212252.7A DE102013212252A1 (de) 2013-06-26 2013-06-26 Turbine und Verfahren zur Anstreiferkennung
PCT/EP2014/062787 WO2014206822A1 (fr) 2013-06-26 2014-06-18 Turbine et procédé de détection de frottement

Publications (1)

Publication Number Publication Date
EP2994617A1 true EP2994617A1 (fr) 2016-03-16

Family

ID=51176336

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14738405.1A Withdrawn EP2994617A1 (fr) 2013-06-26 2014-06-18 Turbine et procédé de détection de frottement

Country Status (7)

Country Link
US (1) US20160138417A1 (fr)
EP (1) EP2994617A1 (fr)
JP (1) JP2016524080A (fr)
KR (1) KR20160023895A (fr)
CN (1) CN105339596A (fr)
DE (1) DE102013212252A1 (fr)
WO (1) WO2014206822A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110159580A (zh) * 2019-05-22 2019-08-23 沈阳透平机械股份有限公司 离心压缩机定子件与叶轮的动态间隙检测设备及检测方法
US20220196807A1 (en) * 2020-12-18 2022-06-23 Ford Global Technologies, Llc Rotating sensor assembly
CN113156250B (zh) * 2021-04-25 2023-08-15 西安交通大学 一种考虑多因素耦合作用的触指损伤模拟分析试验系统及其工作方法

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JPS5672316A (en) * 1979-11-16 1981-06-16 Hitachi Ltd Rubbing position identifier
US4502046A (en) * 1982-06-01 1985-02-26 Westinghouse Electric Corp. System for monitoring metal-to-metal contact in rotating machinery
JP2004052757A (ja) * 2002-05-31 2004-02-19 Toshiba Corp タービン動翼
GB2396438B (en) * 2002-12-20 2006-03-22 Rolls Royce Plc Rotor system
FR2859002A1 (fr) * 2003-08-18 2005-02-25 Snecma Moteurs Dispositif abradable sur carter de soufflante d'un moteur de turbine a gaz
EP1715140A1 (fr) * 2005-04-21 2006-10-25 Siemens Aktiengesellschaft Aube de turbine ayant une bande couvrante et une couche de protection sur la bande couvrante
US20080240902A1 (en) * 2007-03-28 2008-10-02 General Electric Company Method and system for rub detection in a steam turbine
FR2944050B1 (fr) * 2009-04-02 2014-07-11 Turbomeca Roue de turbine a pales desaccordees comportant un dispositif d'amortissement
FR2948736B1 (fr) * 2009-07-31 2011-09-23 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
US20120027582A1 (en) * 2010-08-02 2012-02-02 General Electric Company Floating packing ring assembly

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Also Published As

Publication number Publication date
KR20160023895A (ko) 2016-03-03
US20160138417A1 (en) 2016-05-19
WO2014206822A1 (fr) 2014-12-31
CN105339596A (zh) 2016-02-17
JP2016524080A (ja) 2016-08-12
DE102013212252A1 (de) 2014-12-31

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