EP3540182A1 - Procédé de commande d'une minimisation d'ouverture d'une turbine à gaz - Google Patents

Procédé de commande d'une minimisation d'ouverture d'une turbine à gaz Download PDF

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Publication number
EP3540182A1
EP3540182A1 EP18176962.1A EP18176962A EP3540182A1 EP 3540182 A1 EP3540182 A1 EP 3540182A1 EP 18176962 A EP18176962 A EP 18176962A EP 3540182 A1 EP3540182 A1 EP 3540182A1
Authority
EP
European Patent Office
Prior art keywords
value
gas turbine
gap
max
upper threshold
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Withdrawn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
EP18176962.1A
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German (de)
English (en)
Inventor
Hans-Georg Gamm
Marcus HÜNING
Uwe Kahlstorf
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 US16/976,257 priority Critical patent/US11060412B2/en
Priority to PCT/EP2019/055994 priority patent/WO2019175091A1/fr
Priority to JP2020538123A priority patent/JP6861325B2/ja
Priority to EP19714116.1A priority patent/EP3704354B1/fr
Priority to CN201980018689.1A priority patent/CN111836947B/zh
Publication of EP3540182A1 publication Critical patent/EP3540182A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D17/02—Arrangement of sensing elements
    • F01D17/04—Arrangement of sensing elements responsive to load
    • 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
    • F05D2270/305—Tolerances
    • 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
    • F05D2270/335—Output power or torque
    • 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
    • F05D2270/80—Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges

Definitions

  • the invention relates to a method for controlling a gap minimization of an adjustable gap between a rotor and a housing of a gas turbine, wherein the gas turbine comprises means, in particular hydraulic means, for a gap adjustment.
  • the invention further relates to a control device for carrying out the method and to a gas turbine with such a control device.
  • WO 2014/016153 A1 For example, a method of minimizing an adjustable gap between a blade and a housing of a turbine is known. By displacement of rotor and housing against each other, the gap between the rotor and the housing is to be minimized in a simple manner.
  • an output signal of the rotor and / or the housing associated structure-borne noise monitoring system is used as a measure of the size of the gap and thus to set a minimum gap.
  • Another method for part-load operation of a gas turbine with active hydraulic gap adjustment is for example from WO 2015/128193 A1 known.
  • HCO Hydrophilic Clearance Optimization
  • the invention has for its object to provide an improved HCO logic that allows optimal use of the gap setting especially during a load change during operation of the gas turbine.
  • the object is further achieved according to the invention by a control device for carrying out the method.
  • the object is finally achieved according to the invention by a gas turbine with such a control device.
  • gap minimization means an axial offset of the rotor of the gas turbine against the flow direction, which offset is carried out with the aid of, in particular, the hydraulic means for adjusting the gap between the rotor and the housing.
  • HCO is used in the following text for the term gap minimization.
  • the gap minimization or the HCO function can be activated (the rotor is shifted towards the housing) or deactivated.
  • activated or “deactivated” does not only mean switching on or off of the HCO, but in the case where the gap minimization is already active, "to be activated” is to be equated with “remain activated”. The same applies to an already eliminated gap minimization, in this case “disabled” means "stay disabled”.
  • the invention is based on the consideration to provide a new HCO logic, which is mainly simple and robust, but can minimize the dangers in the operating phases with activated gap optimization.
  • numerous investigations of transient maneuvers were carried out by means of computer simulation, which form the basis for the improved HCO logic.
  • an operating parameter is used, with the aid of which the operating state of the Gas turbine is detected.
  • an operating parameter for example, the power of the gas turbine, a normalized relative power, temperatures or pressures along the main gas channel or temperature and pressure conditions can be used.
  • the operating parameter is chosen so that it responds to a load change.
  • the actual value of the operating parameter is continuously recorded, whereby "continuous" includes both the case of a continuous, uninterrupted, direct measurement or calculation from measured data, as well as the case of a direct measurement or calculation from measured data in short time intervals.
  • the currently detected actual value is compared with the lower and upper threshold values, the course of the actual value being subdivided into at least three operating regimes or ranges: a lower, a middle and an upper range.
  • a maximum value of the actual value over a period of time in the immediate past is recorded. Based on the maximum value, a limit value is determined, which is used when the actual value is in the middle range between the lower and the upper threshold value.
  • the gas turbine In the low load range, the gas turbine is usually only operated for a very short time, if at all, because of the pollutant emissions and the low efficiency. Thus, the efficiency in this load range contributes only very negligibly to the overall efficiency over the operating cycle of the machine. In this respect, there is no need to activate the HCO in this difficult environment. For this reason, the lower threshold is defined for the operating parameter. In the lower area, below the lower threshold, therefore, the gap minimization is deactivated or remains deactivated, if it was not already switched on or already switched off.
  • the analyzes carried out show that in the range of high loads of the gas turbine, in which range the HCO usually is switched on, a tracking or adaptation of the HCO is not required even with load fluctuations.
  • a start from a low-load range is not critical for the use of gap minimization.
  • the upper threshold value for the operating parameter is defined. In the upper area, above the upper threshold, the gap minimization is therefore activated or remains activated, if it was already switched on.
  • the analyzes show that it is in particular the large load reductions in the middle range, which lead to a transient splitting reduction and should thus be accompanied by an HCO deactivation.
  • the ratio of the actual value of the operating parameter to the maximum value of the operating parameter from the immediate past is taken into account. If the difference between the maximum value and the actual value falls below a load-dependent level, which is defined by the limit value, the gap minimization is to be deactivated. Otherwise, the HCO can be activated or remain.
  • the HCO function is activated or deactivated as a function of the behavior of the gas turbine in the predefined period of time.
  • the limit of the operating parameter is used, which depends on the maximum value. If the actual value is above the limit, i. between the threshold and the upper threshold, the gap minimization is or remains activated. However, if the actual value is below the limit, i. between the lower threshold and the limit value, the gap optimization is or remains deactivated.
  • the proposed method results in a very precise activation of the HCO function, whereby several HCO activation hours are obtained during operation of the gas turbine, which has a positive effect on the efficiency of the gas turbine.
  • the method limits the complexity of subdivision of the operating regime of the gas turbine to only three cases. where the HCO logic has to decide if the HCO is turned on or off.
  • the HCO logic described above also provides better match with machine behavior and is independent of active gap measurement.
  • the relative power which is normalized to the rated power of the gas turbine.
  • the relative power is directly coupled to the absolute power, which is well available in the control of the gas turbine and requires no additional hardware effort to be detected.
  • the time interval is between a few tens of minutes and a few hours, in particular between 30 minutes and 90 minutes.
  • the time span is due to the reaction time of the turbine and is thus machine-dependent.
  • the period of time is predetermined in particular in the control of the gas turbine.
  • the lower threshold at a relative power is between 30% and 45%. This means that the gap minimization is switched on, only when at least 30% of the rated power of the gas turbine are reached. Below this relative power, it is provided that the HCO function is permanently inactive.
  • the upper threshold is at a relative power between 50% and 65%. At the latest when 65% of the rated output of the gas turbine is reached, depending on the case, this can also be done at 50% of the nominal power of the gas turbine, the HCO is activated and remains permanently active above the upper threshold.
  • the gap minimization is preferably delayed activated when the actual value exceeds the limit.
  • a time-delayed activation of the HCO prevents a considerable load difference from being bypassed by rapid maneuvers. For this reason, another block of HCO is defined which blocks HCO activation for a period of a few minutes to a maximum of 30 minutes.
  • a plurality of steps for the maximum value are defined between the lower threshold value and the upper threshold value, with only consideration being given for the activation or deactivation of the gap minimization, which is the highest stage which was exceeded by the maximum value in the time interval. In this way, no continuous storage of the maximum value is required each time the maximum value is changed. Only when, for example, increases the gas turbine in a higher power level, it is noted that the gas turbine has been operated above this level. Such a procedure represents a further simplification in the determination of the limit value, since thereby the maximum value remains constant over a longer time.
  • the difference between the limit value and the maximum value is preferably predefined.
  • the relationship between the maximum value and the limit value is specified in particular in the form of a table. This is perfectly adequate for the application, and very reliable and controllable. It is therefore only necessary to know the maximum value of the operating parameter in order to determine the limit value quickly and without great computational effort.
  • a difference between the limit value and the maximum value is preferably predefined for each stage. The respective differences are recorded in the table.
  • the difference between the limit value and the maximum value is determined by calculation. This is done in particular according to a formula stored in the control.
  • the method is advantageously carried out continuously during operation of the gas turbine, as soon as the gas turbine is put into operation.
  • FIG. 1 3 is a graphical representation of the three power ranges into which the power of a gas turbine not shown in detail is subdivided according to the new HCO logic and which is characterized by different operating regimes.
  • the relative power P REL is plotted, which is formed by a current power, which is normalized by the rated power of the gas turbine.
  • the maximum value of the relative power P MAX of the gas turbine is plotted on the Y axis.
  • the three regions U, M and O on the X-axis are separated by a lower threshold P U and an upper threshold P O. Between zero and the lower threshold P U , the power range is marked with U. Above the upper threshold P O the power range is marked with O.
  • the line F which extends over the middle region M, shows the dependence of the limit value P G on the maximum value P MAX .
  • This dependency is stored in the illustrated embodiment in a table, which can be accessed by the controller.
  • the decision as to whether the HCO is activated or deactivated, or remains active or inactive, is based on the development of an actual value P I of the relative power P REL .
  • P I the relative power of the relative power P REL
  • the time span is also stored in the controller and is machine-specific. The time span can also be shorter than 1 hour (eg the measurements of the relative power P REL from the last 45 min are used) or even longer (eg 90 min).
  • the control switches off the gap minimization or, if the gap minimization is already inactive, it remains switched off.
  • the controller activates the gap minimization or, if the gap minimization is already active, it remains switched on.
  • the gap minimization is switched on or off depending on whether the actual value in the range M 'is below the limit value P G or in the range M "above the limit value P G.
  • the limit value P G depends doing so after the maximum value P MAX of the maximum power P MAX in the last hour.
  • the maximum value P MAX To simplify the detection of the maximum value P MAX , several steps can be defined on the Y-axis for the maximum value P MAX , taking into account for activating or deactivating the gap minimization, which is the highest level that is the maximum value P MAX in the last hour was exceeded. For example, between 3 and 10 such stages can be defined, which can also be of different sizes. In particular, the line F looks somewhat different for each stage, ie the predefined or calculated difference between the threshold P G and the maximum value P MAX can vary from stage to stage.
  • a further barrier of HCO can be incorporated which inhibits HCO activation for e.g. Blocked for 15 minutes.
  • the lock engages in particular after a considerable load or. Power increase in the middle range M or in the upper range O, which follows a significant load or power drop in the lower region U.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18176962.1A 2018-03-14 2018-06-11 Procédé de commande d'une minimisation d'ouverture d'une turbine à gaz Withdrawn EP3540182A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US16/976,257 US11060412B2 (en) 2018-03-14 2019-03-11 Method for controlling a gap minimization of a gas turbine
PCT/EP2019/055994 WO2019175091A1 (fr) 2018-03-14 2019-03-11 Procédé de commande de la minimisation d'un intervalle d'une turbine à gaz
JP2020538123A JP6861325B2 (ja) 2018-03-14 2019-03-11 ガスタービンのギャップ最小化を制御する方法
EP19714116.1A EP3704354B1 (fr) 2018-03-14 2019-03-11 Procédé de commande d'une minimisation de jeu d'une turbine à gaz
CN201980018689.1A CN111836947B (zh) 2018-03-14 2019-03-11 用于控制燃气轮机的间隙最小化的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018203896 2018-03-14

Publications (1)

Publication Number Publication Date
EP3540182A1 true EP3540182A1 (fr) 2019-09-18

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Application Number Title Priority Date Filing Date
EP18176962.1A Withdrawn EP3540182A1 (fr) 2018-03-14 2018-06-11 Procédé de commande d'une minimisation d'ouverture d'une turbine à gaz
EP19714116.1A Active EP3704354B1 (fr) 2018-03-14 2019-03-11 Procédé de commande d'une minimisation de jeu d'une turbine à gaz

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Application Number Title Priority Date Filing Date
EP19714116.1A Active EP3704354B1 (fr) 2018-03-14 2019-03-11 Procédé de commande d'une minimisation de jeu d'une turbine à gaz

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US (1) US11060412B2 (fr)
EP (2) EP3540182A1 (fr)
JP (1) JP6861325B2 (fr)
CN (1) CN111836947B (fr)
WO (1) WO2019175091A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115169048A (zh) * 2022-07-22 2022-10-11 东南大学溧阳研究院 一种基于多领域组件建模的重型燃气轮机建模方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113250759A (zh) * 2021-04-30 2021-08-13 上海慕帆动力科技有限公司 一种trt间隙调节***
US11655725B2 (en) 2021-07-15 2023-05-23 Pratt & Whitney Canada Corp. Active clearance control system and method for an aircraft engine

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US20090003991A1 (en) * 2007-06-26 2009-01-01 General Electric Company System and method for turbine engine clearance control with rub detection
EP2236771A2 (fr) * 2009-03-25 2010-10-06 General Electric Company Procédé et appareil pour contrôle de clarté
EP2549065A1 (fr) * 2011-07-18 2013-01-23 General Electric Company Système et procédé d'exploitation d'une turbine
WO2014016153A1 (fr) 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Procédé pour réduire au minimum une fente entre un rotor et un carter
EP2843198A1 (fr) * 2013-08-29 2015-03-04 Rolls-Royce plc Méthode et système de control pour controller activement le jeu à l'extrémité des pales de rotor
WO2015128193A1 (fr) 2014-02-25 2015-09-03 Siemens Aktiengesellschaft Procédé pour faire fonctionner une turbine à gaz avec réglage actif de l'écartement hydraulique

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US4069662A (en) * 1975-12-05 1978-01-24 United Technologies Corporation Clearance control for gas turbine engine
US4230436A (en) * 1978-07-17 1980-10-28 General Electric Company Rotor/shroud clearance control system
US8011883B2 (en) * 2004-12-29 2011-09-06 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
US8126628B2 (en) * 2007-08-03 2012-02-28 General Electric Company Aircraft gas turbine engine blade tip clearance control
US8296037B2 (en) * 2008-06-20 2012-10-23 General Electric Company Method, system, and apparatus for reducing a turbine clearance
US8342798B2 (en) * 2009-07-28 2013-01-01 General Electric Company System and method for clearance control in a rotary machine
US9758252B2 (en) * 2012-08-23 2017-09-12 General Electric Company Method, system, and apparatus for reducing a turbine clearance
US10344614B2 (en) * 2016-04-12 2019-07-09 United Technologies Corporation Active clearance control for a turbine and case

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090003991A1 (en) * 2007-06-26 2009-01-01 General Electric Company System and method for turbine engine clearance control with rub detection
EP2236771A2 (fr) * 2009-03-25 2010-10-06 General Electric Company Procédé et appareil pour contrôle de clarté
EP2549065A1 (fr) * 2011-07-18 2013-01-23 General Electric Company Système et procédé d'exploitation d'une turbine
WO2014016153A1 (fr) 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Procédé pour réduire au minimum une fente entre un rotor et un carter
EP2843198A1 (fr) * 2013-08-29 2015-03-04 Rolls-Royce plc Méthode et système de control pour controller activement le jeu à l'extrémité des pales de rotor
WO2015128193A1 (fr) 2014-02-25 2015-09-03 Siemens Aktiengesellschaft Procédé pour faire fonctionner une turbine à gaz avec réglage actif de l'écartement hydraulique

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115169048A (zh) * 2022-07-22 2022-10-11 东南大学溧阳研究院 一种基于多领域组件建模的重型燃气轮机建模方法

Also Published As

Publication number Publication date
EP3704354A1 (fr) 2020-09-09
CN111836947A (zh) 2020-10-27
JP6861325B2 (ja) 2021-04-21
WO2019175091A1 (fr) 2019-09-19
EP3704354B1 (fr) 2022-06-08
CN111836947B (zh) 2022-10-28
JP2021507176A (ja) 2021-02-22
US20210003027A1 (en) 2021-01-07
US11060412B2 (en) 2021-07-13

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