EP3788246A1 - Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoff - Google Patents
Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoffInfo
- Publication number
- EP3788246A1 EP3788246A1 EP19727869.0A EP19727869A EP3788246A1 EP 3788246 A1 EP3788246 A1 EP 3788246A1 EP 19727869 A EP19727869 A EP 19727869A EP 3788246 A1 EP3788246 A1 EP 3788246A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- gas
- gas turbine
- temperature
- gas line
- 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- Withdrawn
Links
Classifications
-
- 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
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
-
- 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
- F02C9/26—Control of fuel supply
- F02C9/32—Control of fuel supply characterised by throttling of fuel
-
- 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
- F05D2270/20—Purpose of the control system to optimize the performance of a machine
-
- 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
-
- 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
- F05D2270/303—Temperature
Definitions
- the invention relates to a method for operating a gas turbine system with gaseous fuel, which is transported through a gas line to the gas turbine system, burned in a combustion chamber and then fed to a gas turbine.
- the invention further relates to a Steuerervor device for performing the method and a gas turbine with such a control device.
- Gas turbine plants are usually supplied with natural gas as fuel via a gas line.
- the optimal operation of the gas turbine system depends on the quality of the fuel, the right pressure and the right temperature.
- a minimum required pressure which is defined as a prerequisite for the operation of the gas turbine system and must be guaranteed, also depends on various operating and environmental conditions, e.g. Turbine load, ambient temperature, ambient pressure, gas composition, gas temperature, etc. Due to various situations, the pressure in the gas line may not be sufficient, e.g. due to pressure fluctuations in the local gas network, failures in the lines to and in the gas turbine system, failure of the gas compressor, if one is present, fluctuations in the gas quality, pressure losses along the gas line system, increase in the fire output, etc. In the event that the gas turbine combustion depends on the exact distribution of the mass flow of fuel on two or more stages (e.g. main burner and pilot burner), the combustion stability in the above-mentioned situations can no longer be guaranteed.
- the invention is therefore based on the object to overcome the disadvantages of the prior art and to propose an improved method for operating a gas turbine system, in which, in the event of insufficient pressure in the gas line, the power of the gas turbine system is kept as high as possible for as long as possible.
- the object is achieved by a method of a gas turbine system with gaseous fuel, which is transported through a gas line to the gas turbine system, burned in a combustion chamber and then fed to a gas turbine, wherein at least one fitting for flow control of the fuel to the combustion chamber is built in the gas line , whereby a critical opening position is defined for the valve and if the valve is there the critical see exceeding the opening position, a temperature of the fuel in the gas line is reduced.
- control device comprising means for carrying out such a method.
- the object is finally achieved according to the invention by egg gas turbine system with such a control device.
- valve Any device for controlling or regulating the mass flow in the gas line is referred to here as a valve.
- the valve is particularly in a position to completely shut off the gas line so that the gas flow is interrupted.
- the fitting is preferably designed as a control or regulating valve, but it can also be designed in the manner of a flap, a slide or a tap.
- the invention is based on the finding that a particularly reliable controllability of the gas turbine storage unit is sufficient, as a criterion when a lowering of the fuel temperature is required, the position of the
- Flow armature is used.
- the position of the armature is a direct measure of the pressure actually required in front of the combustion chamber or of how far the fuel mass flow can still be raised in response to an insufficient pressure in the gas line. The measures only intervene if this is really necessary, so the set target power of the gas turbine remains unchanged for as long as possible.
- the method is characterized in particular by the fact that it is independent of the load, ie the position of the valve in correlation brought with the critical opening position is a fixed criterion and is independent of the operating point.
- the current position of the valve is always known because the mass flow in the gas line, a part of which the valve is, is known.
- the position of the valve is set depending on the mass flow. This is measured directly or determined indirectly using various parameters. If the valve is in the critical opening position, but the pressure in the gas line is not sufficient, especially since the pressure requirements increase or the pressure in the line decreases, the lowering of the gas temperature must be initiated as a first measure so that the target output is maintained preserved.
- the temperature of the fuel has a significant effect on the pressure in the gas line. By reducing the gas temperature, the density of the gas increases, which leads to lower pressure losses in the fuel system.
- the critical opening position of the valve is preferably in the range above 70% of the maximum opening position.
- the maximum opening position is the position at which the mass flow in the gas line is greatest.
- the decisive, critical opening position of the valve is therefore not necessarily the maximum open position of the valve (however, the critical opening position can also be defined by the maximum opening position), but a position with a slightly minimized flow.
- the advantage here is that quick, short-term changes to the operating parameters, such as Fluctuations in the quality of the fuel can be responded to by opening the valve again.
- the critical opening position can also be subsequently adjusted to the operating conditions by changing it during operation.
- the temperature of the fuel can be reduced via active cooling measures.
- the gas turbine system preferably has a preheating system for the fuel and the temperature of the fuel in the gas line is reduced by reducing the heat supplied to the fuel in the pre-heating system. This is a particularly simple and efficient procedure for lowering the temperature, which requires no additional hardware and is not associated with any energy expenditure.
- a threshold value for the minimum temperature of the fuel is determined taking into account an operating parameter of the gas turbine system and the reduction in the temperature of the fuel in the gas line is stopped when the threshold value is reached.
- an operating parameter is e.g. the NOx value in the exhaust gas, which represents an additional criterion by which it is decided whether the method according to the invention is started or continued.
- Egg ne monitoring of a fixed minimum value of the temperature of the fuel can be provided for gases with increased proportions of higher hydrocarbons, since there is a risk of condensate formation at low gas temperature.
- Threshold for emissions has already been reached, gas cooling is dispensed with as long as the emission value corresponds to the threshold value.
- fittings are installed in the gas line and the position of each of the fittings is used.
- the lines to individual stages for example to the main burner and pilot burner, usually each have a fitting for flow control. If at least one of the fittings is in the critical opening position and can no longer react to growing mass flow requirements, the temperature of the fuel in the gas line is reduced, as already explained.
- a turbine power is preferably additionally reduced. Only when the pressure requirements cannot be met when the valve reaches the critical opening position despite a reduction in temperature, is the turbine output reduced in a controlled manner, in particular by specifying a reduced power setpoint. In emergencies, a gas turbine shutdown can even take place. Both measures, the lowering of the gas temperature and the reduction in output, should be combined with one another in such a way that the output remains unchanged or as high as possible for as long as possible, whereby it must always be ensured that the valve does not exceed the critical opening position.
- a fuel system 2 is shown schematically, which is part of a gas turbine plant, not shown, in which natural gas is used as fuel.
- the gas turbine system generally comprises a compressor, a combustion chamber 4 and a gas turbine, on which e.g. a generator is coupled to generate electricity.
- the fuel system 2 comprises a gas line 6, via which gaseous fuel is fed to the combustion chamber 4.
- gas line 6 via which gaseous fuel is fed to the combustion chamber 4.
- several burners are angeord net, which in the exemplary embodiment shown are formed in several stages and which are symbolically represented by a in the figure
- a branch line 6a, 6b is branched off to each of the burner stages 8, 10, in each of which a control valve 12a, 12b is installed.
- the gas line 6 also includes an emergency valve 14. Upstream of the emergency valve 14, a heat exchanger 16 is also arranged on the gas line 6, which is part of a Vormérmsys system, which serves to preheat the fuel in the gas line 6.
- the gas turbine system further comprises a control or regulating device 18 which, among other things, regulates the position of the regulating valves 12a, 12b.
- a critical opening position for the control valves 12a, 12b is stored, which is, for example, 80% of a maximum opening position of the control valves 12a, 12b.
- the critical opening position can, for example, also be 70%, 75%, 85%, 90%, 95% of the maximum opening position of the control valves 12a, 12b or correspond to the maximum opening position.
- the course of the method according to the invention can be seen from FIG. 2.
- the position of the respective control valve 12a, 12b is always set via a control circuit in the control or regulating device 18 in such a way that the gas turbine runs at a predetermined power or combustion temperature. It thus automatically reacts indirectly to fluctuations in the following sizes: natural gas supply pressure, natural gas temperature, natural gas quality, ambient conditions,
- a decreasing fuel supply pressure BD here natural gas supply pressure
- a deteriorating gas quality instead of a falling ambient temperature, a rising ambient air humidity, a rising ambient pressure, contamination of the burner or natural gas system components, a reduced gas turbine efficiency, etc. could alternatively be used.
- the fuel supply pressure BD is constant from the point in time to to the point in time ti, a control valve position RV is below a critical opening position S crit .
- the fuel temperature T B and the turbine power P remain stable at their target value (P s for the turbine power).
- the fuel supply pressure BD in the gas line 6 drops from ti to t 2 .
- the corresponding control valve or both control valves 12a, 12b is opened further until a critical opening position S crit is reached.
- the fuel supply pressure BD stabilizes at a lower level than the original one.
- the control valves 12a, 12b are still in the critical opening position S crit .
- the turbine power P has been below the power setpoint P s since t 3 , but in parallel with the progressive reduction in the fuel temperature T B, the gas turbine power P slowly returns to the setpoint P s raised. It should be ensured that the fuel temperature T B remains above a minimum threshold value T min , the threshold value T min correlating, for example, with the NOx emissions or another operating parameter of the gas turbine system.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18182564.7A EP3594475A1 (de) | 2018-07-10 | 2018-07-10 | Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoff |
PCT/EP2019/062589 WO2020011426A1 (de) | 2018-07-10 | 2019-05-16 | Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoff |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3788246A1 true EP3788246A1 (de) | 2021-03-10 |
Family
ID=62916453
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18182564.7A Withdrawn EP3594475A1 (de) | 2018-07-10 | 2018-07-10 | Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoff |
EP19727869.0A Withdrawn EP3788246A1 (de) | 2018-07-10 | 2019-05-16 | Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoff |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18182564.7A Withdrawn EP3594475A1 (de) | 2018-07-10 | 2018-07-10 | Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoff |
Country Status (6)
Country | Link |
---|---|
US (1) | US11242807B2 (de) |
EP (2) | EP3594475A1 (de) |
JP (1) | JP6999858B2 (de) |
KR (1) | KR102346323B1 (de) |
CN (1) | CN112513442B (de) |
WO (1) | WO2020011426A1 (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113483357B (zh) * | 2021-07-06 | 2022-06-21 | 中国人民解放军国防科技大学 | 一种固定压力变位置的气体燃料喷注系统 |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB763448A (en) * | 1953-09-09 | 1956-12-12 | Rolls Royce | Improvements in or relating to gas turbine engine fuel systems |
JPH1193694A (ja) * | 1997-09-18 | 1999-04-06 | Toshiba Corp | ガスタービンプラント |
JP3836604B2 (ja) * | 1998-07-23 | 2006-10-25 | 株式会社日立製作所 | ガスタービン燃料ガス減圧加温装置 |
WO2005095861A1 (de) | 2004-03-31 | 2005-10-13 | Alstom Technology Ltd | Verfahren zum betreiben einer wärmekraftmaschine, vorzugsweise einer gasturbinenanlage |
EP1956294A1 (de) * | 2007-02-06 | 2008-08-13 | Siemens Aktiengesellschaft | Feuerungsanlage und Verfahren zum Betrieb einer Feuerungsanlage |
JP4495179B2 (ja) * | 2007-02-28 | 2010-06-30 | 三菱重工業株式会社 | 燃料ノズル装置、ガスタービンおよび燃料ノズル装置の制御方法 |
US20100307157A1 (en) * | 2009-06-08 | 2010-12-09 | General Electric Company | Methods relating to turbine engine control and operation |
FR2970303B1 (fr) * | 2011-01-06 | 2014-06-13 | Snecma | Circuit de carburant de turbomachine aeronautique a vanne de regulation de pression de carburant |
JP5984435B2 (ja) * | 2012-03-06 | 2016-09-06 | 三菱日立パワーシステムズ株式会社 | ガスタービン制御装置及び制御方法 |
JP2013249755A (ja) * | 2012-05-31 | 2013-12-12 | Hitachi Ltd | 高湿分空気利用ガスタービン |
US9291098B2 (en) * | 2012-11-14 | 2016-03-22 | General Electric Company | Turbomachine and staged combustion system of a turbomachine |
US20160060554A1 (en) * | 2014-09-03 | 2016-03-03 | Bha Altair, Llc | Gaseous Fuel Wobbe Index Modification Skid |
US10006366B2 (en) * | 2015-04-28 | 2018-06-26 | United Technologies Corporation | Fuel recirculation thermal management system |
CN107178789B (zh) | 2016-03-09 | 2020-06-09 | 西门子公司 | 天然气燃烧器的燃烧监控方法、装置和系统 |
-
2018
- 2018-07-10 EP EP18182564.7A patent/EP3594475A1/de not_active Withdrawn
-
2019
- 2019-05-16 JP JP2021500441A patent/JP6999858B2/ja active Active
- 2019-05-16 EP EP19727869.0A patent/EP3788246A1/de not_active Withdrawn
- 2019-05-16 CN CN201980046041.5A patent/CN112513442B/zh not_active Expired - Fee Related
- 2019-05-16 WO PCT/EP2019/062589 patent/WO2020011426A1/de unknown
- 2019-05-16 KR KR1020217003676A patent/KR102346323B1/ko active IP Right Grant
- 2019-05-16 US US17/257,578 patent/US11242807B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
KR102346323B1 (ko) | 2022-01-03 |
CN112513442B (zh) | 2021-08-31 |
US11242807B2 (en) | 2022-02-08 |
EP3594475A1 (de) | 2020-01-15 |
KR20210019113A (ko) | 2021-02-19 |
WO2020011426A1 (de) | 2020-01-16 |
CN112513442A (zh) | 2021-03-16 |
JP2021524555A (ja) | 2021-09-13 |
JP6999858B2 (ja) | 2022-01-19 |
US20210246839A1 (en) | 2021-08-12 |
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