WO2005095861A1 - Verfahren zum betreiben einer wärmekraftmaschine, vorzugsweise einer gasturbinenanlage - Google Patents
Verfahren zum betreiben einer wärmekraftmaschine, vorzugsweise einer gasturbinenanlage Download PDFInfo
- Publication number
- WO2005095861A1 WO2005095861A1 PCT/EP2005/051382 EP2005051382W WO2005095861A1 WO 2005095861 A1 WO2005095861 A1 WO 2005095861A1 EP 2005051382 W EP2005051382 W EP 2005051382W WO 2005095861 A1 WO2005095861 A1 WO 2005095861A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas
- pressure
- fuel
- heat engine
- load state
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000007789 gas Substances 0.000 claims abstract description 188
- 239000000446 fuel Substances 0.000 claims abstract description 94
- 238000002485 combustion reaction Methods 0.000 claims abstract description 55
- 230000009467 reduction Effects 0.000 claims abstract description 15
- 239000000203 mixture Substances 0.000 claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 12
- 230000001105 regulatory effect Effects 0.000 claims abstract description 7
- 230000001419 dependent effect Effects 0.000 claims description 14
- 230000006641 stabilisation Effects 0.000 claims description 8
- 238000011105 stabilization Methods 0.000 claims description 8
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 230000000087 stabilizing effect Effects 0.000 abstract 2
- 238000010586 diagram Methods 0.000 description 11
- 230000002427 irreversible effect Effects 0.000 description 5
- 230000007423 decrease Effects 0.000 description 4
- 230000009977 dual effect Effects 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 230000000977 initiatory effect Effects 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000004224 protection Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
-
- 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
-
- 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
- F02C9/46—Emergency fuel control
-
- 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
- F05D2270/09—Purpose of the control system to cope with emergencies
-
- 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 heat engine, preferably a gas turbine system, in which hot gases are generated by firing a combustion chamber, the kinetic flow energy of which, at least partially, flows through a rotary machine in rotary energy and ultimately through a generator arrangement connected to the rotary machine into electrical energy for feeding is converted into a power grid.
- Some gas turbine plants provide so-called fuel compressor stages, by means of which the supply gas pressure can always be kept at a pressure level which ensures the safe operation of the gas turbine plant.
- Such fuel compressor stages can be switched on if necessary so that in the event of a drop in the supply gas pressure relative to the required variable gas pressure, which not only depends on the load state of the gas turbine, but is also subject to other parameters such as, for example, the ambient temperature, fuel temperature and air humidity just to name a few to stabilize the supply gas pressure to a required pressure level.
- the use of energy-consuming fuel compressor stages is to be avoided in order to be able to maintain the operation of the heat engine largely without drastic energy losses, even in the event of a drop in the fuel supply pressure.
- the high security standards also apply, which are placed on a heat engine in operation to be fulfilled without restriction.
- the general idea of the invention relates in principle to all heat engines in which hot gases are generated by burning gaseous fuel within a combustion chamber, by which a rotary unit is driven, the rotational energy of which is converted into a further form of energy, preferably into electrical energy.
- the rotation energy inherent in the rotation unit represents the so-called load state of the heat engine, which can be set by regulating the amount of the gaseous fuel supplied to the combustion and can be regarded as an equivalent quantity for the electrical energy fed into a power supply network.
- the load state must be adjusted accordingly by regulating the fuel supply.
- there are also other measures known for increasing the performance of heat engines by means of which the combustion process can be optimized without increasing the fuel supply itself.
- the mass flow can be increased and the volume of the hot gases generated by the combustion process can be increased.
- the steam feed serves to cool all of the system components involved in the combustion process.
- Another measure to increase performance is provided by cooling the combustion air supplied to the combustion process. This means that colder air has a higher density and therefore a higher proportion of oxygen than warmer air. It is evident that the combustion process takes place in the presence of larger amounts of oxygen with better burnout results. Targeted cooling of the gaseous fuel supplied to the combustion process also contributes to increasing the fuel density and thus increasing the burner efficiency.
- the method according to the preamble of claim 1, in return for previous measures that contribute to the stabilization of the fuel supply pressure and to protect the entire gas turbine system from irreversible damage, provides for those measures in a first step when a pressure drop in the fuel supply pressure occurs throttle or switch off completely, which contribute to the increase in performance of the gas turbine system and do not affect the amount of fuel supplied to the combustion process.
- the heat engine is normally operated under a load condition, provided that the gaseous fuel is supplied to the combustion through the supply gas line under a gas pressure p ⁇ as that is greater than a critical pressure value p ac tioniimits, which itself depends on the load condition of the gas turbine system. If it occurs that the supply gas pressure pGas drops to the critical pressure value Pactioniimit, at least one of the following measures will be initiated according to the invention in a first step: throttling the cooling of the combustion air, which is brought to combustion for the mixture formation, throttling the Water vapor admixture in the fuel-air mixture to be burned and throttling of the cooling of the water vapor to be admixed with the fuel-air mixture.
- the fuel temperature is actively reduced in a second step.
- a reduction in the fuel temperature leads to a decrease in the fuel volume flow due to the increase in the fuel density and at the same time to a reduction in the pressure losses within the fuel supply.
- This measure automatically reduces the load that prevails in the initial load state, whereby the system-related combustion chamber pressure automatically decreases.
- the pressure difference between the two pressure levels enables a kind of buffer area through which the further behavior of the in the
- the further method either provides for a complete criterion based on a decision criterion and terminates the standard load and returns the gas turbine system to the initial load state Carry out emergency relief in which the fuel reduction occurs more rapidly than in the case of standard relief, or arrange for the fuel supply to be switched to a different fuel type, provided the gas turbine system has a dual fuel supply.
- FIG. 1 flow chart to illustrate the method
- FIG. 1 shows a decision flow diagram, on the basis of which the method according to the invention is to be explained.
- the diagram does not take into account the normal case in which the gas turbine system operates under pressure conditions in which the gas supply pressure is always above a system-related minimum pressure level. However, if the gas pressure falls below the minimum pressure level p ac tioniimit ⁇ , all measures to increase performance are throttled or completely switched off in a first step I, ie cooling of the combustion air (KV), which is brought to the mixture with the fuel for combustion, water vapor admixture (WB) in the fuel-air mixture to be burned and cooling of the water vapor (KW) to be added to the fuel-air mixture.
- KV combustion air
- WB water vapor admixture
- the gas turbine system experiences a change in the operating range, which is equivalent to an increase in the ambient temperature T.
- the gas pressure p Ga s in the supply line stabilize as a result relative to the minimum pressure level Pactioniimit, the above measures can be maintained or can be successively reversed while observing the gas pressure.
- the fuel temperature TB is actively reduced in step II. A reduction in the fuel temperature leads to a decrease in the fuel volume flow BV due to the increase in the fuel density and at the same time to a reduction in the pressure losses within the fuel supply.
- step III a controlled load (GA) of the gas turbine system takes place in step III, which is initiated for reasons of avoiding damage, the gas turbine system is brought into an operationally safe state (save) and further with reference to FIG. 2 is described.
- FIG. 2 shows a p / L diagram in which the pressure p is plotted along the ordinate and the load state L along the abscissa.
- Psafety margin Psystem-requirement "3 + 1 bar
- Pioading hysteresis Psystem-requirement” 3 + 1, 3 bar SOWI ⁇
- Pprotection Iimit Psystem-requirement "3 ⁇ 0.0 bar.
- the gas turbine system is automatically based on a standardized fuel throttling with a throttling rate ri dependent on the respective gas turbine system.
- the pressure line p sa fety margin serves as an always higher than the reference pressure line Paction IM lying safety pressure level. If the gas pressure p gas adjusts to the safety pressure level Psafety margin due to a reduced fuel supply in a reduced load condition Li, the standard load is ended. Does the gas pressure p gas remain constant even after the standard load and maintains the pressure level p sa f et ym a ram in the load state L
- the standard load is repeated repeatedly to a further reduced load state L 2 (not shown in the diagram).
- the gas pressure p gas itself is like the ruling on this load level security printing p sa ttey ma r in to the reduced load condition L 2, the standard has been downsized quits again. If the gas pressure p gas stabilizes, a load build-up from the load state L 2 to the initial load state Lo is started.
- the scenario described above describes the case of a slow pressure loss in the fuel supply line, in which a fuel throttling usually leads to a constant gas pressure p gas by means of a standard load, which stabilizes again when the safety pressure level psafetymatgin is reached in a reduced load state Li and opens up the possibility of transferring the gas turbine system in the initial load state.
- the reference pressure Pactioniimi t is reached relatively quickly in the initial load state L 0 .
- the standard load described above is carried out automatically by throttling the fuel supply.
- the gas pressure p gas does not remain constant in spite of the standard load, but continues to drop dynamically, but this more slowly than the reference pressure value p a c «on iimit which drops due to the standard load Standard load always p Gas > Paction iimit (L) -
- the load state U can be carried out as part of a standard load structure be returned to the initial load state L 0 .
- the standard load structure is discussed in more detail below.
- an emergency shutdown is unavoidable to avoid irreversible system damage.
- an emergency shutdown in the case of a dual fuel supply to the gas turbine system, it is possible to switch from supplying the combustion process with gaseous fuel to liquid fuel operation.
- the fuel supply is carried out with a much greater throttle rate r 2 than in the case of a standard relief.
- the throttle rate r 2 in the event of an emergency relief is at least 6 times, preferably at least 10 times the throttle rate ri used in the standard relief.
- the gas turbine system has to be returned to the original initial load state L 0 .
- this is done as part of a standard load structure, which, as can be seen from the diagram (see dotted line 4), is carried out in stages he follows.
- the initial load state L 0 at which the pressure drop occurred in the fuel supply line, is stored in the system, so that the initial load state can be restored in a targeted manner after corresponding standard unloading.
- the reduced load state assumed by way of the standard load is L 5 , at which the gas pressure p gas has reached the safety pressure p sa f ⁇ t ym a ⁇ gin and the load level L 5 remains at the pressure level
- Pioading hysteresis increases, for which the following applies: pioading hysteresis Psafety margin, whereby the pressure level
- PLoading hysteresis test is greater than the security pressure level psafety margin.
- the method is particularly reliable in countries and regions in which the supply of gaseous fuel is subject to fluctuations Operating mode of gas-fired heat engines, in particular gas turbine systems.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE502005007618T DE502005007618D1 (de) | 2004-03-31 | 2005-03-24 | Verfahren zum Betreiben einer Wärmekraftmaschine, Vorzugsweise einer Gasturbinenanlage |
EP05717146A EP1730444B1 (de) | 2004-03-31 | 2005-03-24 | Verfahren zum Betreiben einer Wärmekraftmaschine, Vorzugsweise einer Gasturbinenanlage |
AT05717146T ATE435366T1 (de) | 2004-03-31 | 2005-03-24 | Verfahren zum betreiben einer wärmekraftmaschine, vorzugsweise einer gasturbinenanlage |
US11/529,626 US7434403B2 (en) | 2004-03-31 | 2006-09-29 | Method of operating a thermal power plant |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH556/04 | 2004-03-31 | ||
CH5562004 | 2004-03-31 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/529,626 Continuation US7434403B2 (en) | 2004-03-31 | 2006-09-29 | Method of operating a thermal power plant |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005095861A1 true WO2005095861A1 (de) | 2005-10-13 |
Family
ID=34962522
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2005/051382 WO2005095861A1 (de) | 2004-03-31 | 2005-03-24 | Verfahren zum betreiben einer wärmekraftmaschine, vorzugsweise einer gasturbinenanlage |
Country Status (6)
Country | Link |
---|---|
US (1) | US7434403B2 (de) |
EP (1) | EP1730444B1 (de) |
AT (1) | ATE435366T1 (de) |
DE (1) | DE502005007618D1 (de) |
ES (1) | ES2327855T3 (de) |
WO (1) | WO2005095861A1 (de) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9279370B2 (en) | 2011-10-28 | 2016-03-08 | General Electric Company | Turbomachine and method of operating a turbomachine to perform a fuel change over at a high load |
EP3594475A1 (de) | 2018-07-10 | 2020-01-15 | Siemens Aktiengesellschaft | Verfahren zum betreiben einer gasturbinenanlage mit gasförmigem brennstoff |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE846038C (de) * | 1946-04-03 | 1952-08-07 | Brown Ag | Druckgasbetriebene Waermekraftanlage, z. B. Erdgasturbine |
DE4211681A1 (de) * | 1991-04-09 | 1992-10-15 | Kawasaki Heavy Ind Ltd | Verfahren zum steuern des abbrennens eines brenngases |
US6145318A (en) * | 1998-10-22 | 2000-11-14 | General Electric Co. | Dual orifice bypass system for dual-fuel gas turbine |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1093793A (en) | 1965-03-30 | 1967-12-06 | Francis Tin Chak Ma | Improvements in and relating to gas turbine engines |
JP3039947B2 (ja) * | 1990-03-19 | 2000-05-08 | 株式会社日立製作所 | ガスタービンの燃料制御装置 |
DE4221805A1 (de) | 1992-07-03 | 1994-01-05 | Mak System Gmbh | Verfahren und Einrichtung zum Starten einer Gasturbine |
JP3658415B2 (ja) * | 1993-12-28 | 2005-06-08 | 株式会社 日立インダストリイズ | ガスタービン装置 |
AU730820B2 (en) * | 1995-12-26 | 2001-03-15 | Kabushiki Kaisha Toshiba | Fuel supply apparatus for gas turbine and control unit for the same |
DE19549141A1 (de) | 1995-12-29 | 1997-07-03 | Asea Brown Boveri | Verfahren zum Betrieb einer Gasturbogruppe mit niederkalorischem Brennstoff |
US6484490B1 (en) * | 2000-05-09 | 2002-11-26 | Ingersoll-Rand Energy Systems Corp. | Gas turbine system and method |
JP3881871B2 (ja) | 2001-11-13 | 2007-02-14 | 三菱重工業株式会社 | ガスタービンの燃料制御方法、及びそれに供する制御装置 |
-
2005
- 2005-03-24 AT AT05717146T patent/ATE435366T1/de not_active IP Right Cessation
- 2005-03-24 WO PCT/EP2005/051382 patent/WO2005095861A1/de not_active Application Discontinuation
- 2005-03-24 EP EP05717146A patent/EP1730444B1/de not_active Not-in-force
- 2005-03-24 DE DE502005007618T patent/DE502005007618D1/de active Active
- 2005-03-24 ES ES05717146T patent/ES2327855T3/es active Active
-
2006
- 2006-09-29 US US11/529,626 patent/US7434403B2/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE846038C (de) * | 1946-04-03 | 1952-08-07 | Brown Ag | Druckgasbetriebene Waermekraftanlage, z. B. Erdgasturbine |
DE4211681A1 (de) * | 1991-04-09 | 1992-10-15 | Kawasaki Heavy Ind Ltd | Verfahren zum steuern des abbrennens eines brenngases |
US6145318A (en) * | 1998-10-22 | 2000-11-14 | General Electric Co. | Dual orifice bypass system for dual-fuel gas turbine |
Also Published As
Publication number | Publication date |
---|---|
US20070062200A1 (en) | 2007-03-22 |
DE502005007618D1 (de) | 2009-08-13 |
EP1730444B1 (de) | 2009-07-01 |
ES2327855T3 (es) | 2009-11-04 |
EP1730444A1 (de) | 2006-12-13 |
ATE435366T1 (de) | 2009-07-15 |
US7434403B2 (en) | 2008-10-14 |
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