EP1996807A1 - Procédé de vérification d'une installation de turbine et dispositif correspondant - Google Patents

Procédé de vérification d'une installation de turbine et dispositif correspondant

Info

Publication number
EP1996807A1
EP1996807A1 EP07704158A EP07704158A EP1996807A1 EP 1996807 A1 EP1996807 A1 EP 1996807A1 EP 07704158 A EP07704158 A EP 07704158A EP 07704158 A EP07704158 A EP 07704158A EP 1996807 A1 EP1996807 A1 EP 1996807A1
Authority
EP
European Patent Office
Prior art keywords
determined
state
measuring device
turbine
actual
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Withdrawn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
EP07704158A
Other languages
German (de)
English (en)
Inventor
Ulrich Ehehalt
Scarlett Fajardo-Reina
Daniel Grundei
Harald Harders
Stefan Krause
Martin Krompietz
Andreas Lüttenberg
Christoph Pels Leusden
Wilhelm Scheidtmann
Eckart Schumann
Thomas-Dieter Tenrahm
Dirk Trenaman
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP07704158A priority Critical patent/EP1996807A1/fr
Publication of EP1996807A1 publication Critical patent/EP1996807A1/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Withdrawn legal-status Critical Current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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/14—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object using acoustic emission techniques
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2260/80—Diagnostics
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3015—Pressure differential pressure
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/26—Scanned objects
    • G01N2291/269—Various geometry objects
    • G01N2291/2693—Rotor or turbine parts

Definitions

  • the invention relates to a method for the inspection of energy conversion machines, in particular a gas turbine plant or a steam turbine plant.
  • the invention further relates to an inspection system for a turbine system for carrying out the method according to the invention.
  • turbine systems are subject to a total inspection due to an empirical size valid for the entire turbine, which typically shuts down the entire turbine system.
  • the guide and rotor blades or combustion chamber liners are examined in more detail to determine whether the state of the components allows further use of these components in turbine plant operation or optionally a replacement or overhaul ⁇ the components is required to prevent accidents during operation of the turbine plant vorzu ⁇ bow.
  • an effective operating time (abbr.: EOH), which is calculated by means of empirical formulas, can serve as a decisive parameter for establishing the maintenance stoppages.
  • the following input variables are conceivable: the operating hours of the turbine system (abbreviation: OH), so-called dynamic hours
  • EP 1 227 222 A2 discloses a method for determining a service time of a gas turbine.
  • the service time is determined as a function of the wear of a monitored turbine blade, wherein the wear of the turbine blade is determined by means of a temperature sensor.
  • DE 198 43 615 A1 discloses a service control unit for calculating and displaying the due date of the next service of a
  • the service control unit observes the time behavior of the actual values of operating signals or parts thereof (such as the rotor speed) and draws conclusions therefrom on a soon to be necessary inspection.
  • the invention has for its object to provide a method for inspecting a turbine system, with which the
  • the determined actual state of the respective component can then be compared at any time during ongoing turbine operation with a predetermined desired state.
  • comparison between the actual state and a predetermined desired state, which corresponds to a gantaugli ⁇ chen state of the relevant component of the turbine system can then be derived according to the invention, whether a total inspection of the turbine system is required, in which the turbine system in the Usually shut down.
  • the relevant components and other critical components can then be reintroduced. be examined for their suitability for use. Under certain circumstances, it may be necessary to replace corresponding components or to carry out a suitable repair.
  • the at least one component of the turbine installation comprises the compressor's guide vanes which can be adjusted relative to the outflow, the actual state to be determined being the angular position of the guide vanes relative to the inflow direction, and the means
  • Image recording device in particular a camera, wherein for determining the angular position by means of the image recording device image captures of the guide vane are made to make the decision of the overall inspection of their condition.
  • the adjustable angular position of vanes in particular of adjustable vanes in compressors, may be displaced by mechanical or thermal loads under circumstances, which may adversely affect the efficiency of the turbine.
  • the actual state characterized by the angular position of the guide vanes relative to the inflow direction, can be determined using an image pickup device, in particular a camera, and compared directly with corresponding specifications for uniform angular positions that comprise the desired state.
  • a further monitored during operation component of the turbine system is a filter, the actual state to be determined the state of contamination of the filter, and the associated means a pressure measuring device, wherein for determining the contamination state of the filter, the pressure drop over the filter, which adjusts itself when flowing through the filter, is measured by means of the pressure measuring device.
  • the filter is preferably an intake filter in an intake of the compressor of a turbine plant.
  • the Verschmutzungszu ⁇ was directly related to the pressure drop across the filter in a known manner in the context, and therefore can be inventively during ongoing turbine operation quanti ⁇ fied.
  • the measurement of the pressure drop takes place by means of a customary pressure measuring device. Is in this practical development of the method of the so ermit- Telte actual state compared to the target state in the form of a specified differently value or value range for the pressure drop. Is an intolerable deviation determined from the set ⁇ worth handicap, the turbine plant for through ⁇ leadership of an overall inspection shutdown at which the suction filter from the intake housing to remove and with a new or refurbished suction filter must be replaced.
  • the degree of soiling of an external filter in the cooling circulation of a turbine installation which is determined by a pressure drop measurement, also permits conclusions about the degree of soiling or burnup of the blades.
  • Thermographietician is performed, which is carried out using the Thermographiemess learned.
  • thermography measurement By means of a thermography measurement on the guide vanes and / or rotor blades of the first turbine stage, the actual condition of the blades can be determined in the form of their material properties.
  • a thermographic measurement enables the detection of film chipping, cracks and scaling on the blades.
  • the target state includes this example ⁇ a corresponding use suitable blade whose Schichtabplatzungen scalings and have an extent can be ensured with the still a safe use of the blade over a sufficiently long period of operation.
  • the target state can information on the Ge ⁇ Stalt, particularly the length nor uncritical cracks umfas ⁇ sen, which can for the evaluation of the current situation compared to the measured cracks are.
  • a structure-borne noise measuring device can be used with which determine the above material fatigue characteristics of the blades, in particular cracks and quantify their extent by a structure-borne noise measurement.
  • Combustion liners and heat shields in particular ceramic heat shields and metallic heat shields are determined and, as stated above, to assess the material properties are compared with corresponding desired states.
  • the structure-borne noise measuring device as obtained with the thermographic measuring device measuring results may according to the invention matched or are combined together, then the jewei ⁇ actual states of the above components to determine with the utmost precision and through subsequent comparison with corresponding desired conditions for a meaningful assessment allow the actual conditions that may require a total inspection of the turbine system.
  • the invention further relates to an inspection system for a turbine installation for carrying out the method according to the invention, having at least one means which is provided for determining an actual state of at least one selected component of the turbine installation, and at least one evaluation unit which is designed to receive the actual state determined by the at least one means, evaluate it and compare it with at least one predetermined desired state, wherein the evaluation unit is further configured in a preferred embodiment based on the comparison between the determined actual state and target state To ⁇ stance to deduce whether a total inspection of the turbine is required.
  • a plurality of different components are monitored simultaneously, in which case, if necessary, other desired states for the individual components can be predetermined. If wear occurs with two or more components, an earlier overall inspection may be useful compared to later overall inspection initiated by a single component.
  • the actual state of the respective component of the turbine system is first determined by means of a suitable measuring device (see step S1). Subsequently, the ascertained actual state is compared with a predetermined desired state (compare step S2). In the next step (see. Step S3) is decided on the basis of the comparison whether a Rescueinspek ⁇ tion of the turbine installation is required, wherein the Turbi ⁇ nena position shut down and corresponding components will be replaced or be repaired again. If not, an estimation is made for the still-to-be-expected service life, for example by means of a crack propagation model, or an estimate for the remaining possible duration of use.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

La présente invention concerne un procédé de vérification, en particulier pour une installation de turbine à gaz ou pour une installation de turbine à vapeur. Ce procédé consiste à détecter un état réel d'un composant de l'installation de turbine à l'aide d'un système adapté, à comparer l'état réel détecté à un état théorique prédéfini du composant, puis, sur la base de cette comparaison entre l'état réel et l'état théorique, à déduire si une vérification globale de l'installation de turbine est nécessaire. Ledit composant consiste en une aube directrice dont la position angulaire par rapport à la direction d'entrée représente l'état réel à détecter. Cet état réel est déterminé au moyen d'un dispositif de prise de vue. Cette invention concerne également un système de vérification de turbine pour mettre en oeuvre ledit procédé.
EP07704158A 2006-03-17 2007-01-26 Procédé de vérification d'une installation de turbine et dispositif correspondant Withdrawn EP1996807A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07704158A EP1996807A1 (fr) 2006-03-17 2007-01-26 Procédé de vérification d'une installation de turbine et dispositif correspondant

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06005567A EP1835150A1 (fr) 2006-03-17 2006-03-17 Procédé et dispositif d'inspection d'une installation de turbine
PCT/EP2007/050767 WO2007107395A1 (fr) 2006-03-17 2007-01-26 Procédé de vérification d'une installation de turbine et dispositif correspondant
EP07704158A EP1996807A1 (fr) 2006-03-17 2007-01-26 Procédé de vérification d'une installation de turbine et dispositif correspondant

Publications (1)

Publication Number Publication Date
EP1996807A1 true EP1996807A1 (fr) 2008-12-03

Family

ID=36822326

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06005567A Withdrawn EP1835150A1 (fr) 2006-03-17 2006-03-17 Procédé et dispositif d'inspection d'une installation de turbine
EP07704158A Withdrawn EP1996807A1 (fr) 2006-03-17 2007-01-26 Procédé de vérification d'une installation de turbine et dispositif correspondant

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06005567A Withdrawn EP1835150A1 (fr) 2006-03-17 2006-03-17 Procédé et dispositif d'inspection d'une installation de turbine

Country Status (3)

Country Link
US (1) US8322202B2 (fr)
EP (2) EP1835150A1 (fr)
WO (1) WO2007107395A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9970325B2 (en) 2015-04-30 2018-05-15 General Electric Company Jacking assembly for rotor

Families Citing this family (5)

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US20110106747A1 (en) * 2009-10-30 2011-05-05 General Electric Company Turbine life assessment and inspection system and methods
US8695445B2 (en) 2011-05-09 2014-04-15 General Electric Company Wear-indicating system for use with turbine engines and methods of inspecting same
DE102011114541A1 (de) * 2011-09-30 2013-04-04 Lufthansa Technik Ag Endoskopiesystem und korrespondierendesVerfahren zur Untersuchung von Gasturbinen
US9453430B2 (en) * 2014-03-21 2016-09-27 Siemens Energy, Inc. Method for tracking turbine blade creep
CN119987335B (zh) * 2025-04-15 2025-09-19 大唐苏州热电有限责任公司 一种燃气轮机系统的故障诊断方法及装置

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9970325B2 (en) 2015-04-30 2018-05-15 General Electric Company Jacking assembly for rotor
US10344625B2 (en) 2015-04-30 2019-07-09 General Electric Company Jacking assembly for rotor

Also Published As

Publication number Publication date
US8322202B2 (en) 2012-12-04
WO2007107395A1 (fr) 2007-09-27
US20090293596A1 (en) 2009-12-03
EP1835150A1 (fr) 2007-09-19

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