WO2014128000A1 - Verfahren zum betreiben einer gasturbine unterhalb ihrer nennleistung - Google Patents
Verfahren zum betreiben einer gasturbine unterhalb ihrer nennleistung Download PDFInfo
- Publication number
- WO2014128000A1 WO2014128000A1 PCT/EP2014/052310 EP2014052310W WO2014128000A1 WO 2014128000 A1 WO2014128000 A1 WO 2014128000A1 EP 2014052310 W EP2014052310 W EP 2014052310W WO 2014128000 A1 WO2014128000 A1 WO 2014128000A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas turbine
- temperature
- exhaust gas
- turbine
- gas
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000002485 combustion reaction Methods 0.000 claims abstract description 43
- 239000007788 liquid Substances 0.000 claims abstract description 9
- 239000000446 fuel Substances 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 90
- 239000003570 air Substances 0.000 description 8
- 239000000463 material Substances 0.000 description 5
- 238000011084 recovery Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000004904 shortening Methods 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
-
- 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
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
-
- 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
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
-
- 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
- F02C7/16—Cooling of plants characterised by cooling medium
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
- F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
-
- 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
- F05D2270/08—Purpose of the control system to produce clean exhaust gases
- F05D2270/083—Purpose of the control system to produce clean exhaust gases by monitoring combustion conditions
Definitions
- the invention relates to a method for operating a gas turbine below its rated power, in which lowering of the output gas turbine power, a CO emission increases in the exhaust gas of the gas turbine, wherein upon reaching a predetermined limit for the CO emission or falls below a predetermined limit for the votes Gas turbine power is increased combustion temperature in the combustion chamber of the gas turbine.
- DE 10 2008 044 442 A1 known from the prior art proposes equipping such gas turbines with a bypass system, through which a portion of the compressor discharge air passes by the combustion chamber and into the exhaust gas duct the gas turbine can be fed. Thereby, the amount of air supplied to the combustion can be reduced, which raises the combustion temperature and thus the relevant primary zone temperature.
- the object of the invention is therefore to provide a method for operating a gas turbine which, despite a partial load operation, has a comparatively high efficiency with C0-emission-compliant operation.
- Another object of the invention is to provide a method in which the gas turbine operation compliant with emissions is expanded to lower loads.
- the gas turbine in the method for operating a gas turbine below its rated power, in which with the lowering of the emitted gas turbine power, a CO emission in the exhaust gas of the gas turbine increases, upon reaching a (arbitrary) predetermined limit value for the CO emission or falls below a relative or absolute specified limit value for the delivered gas turbine power, the combustion temperature in the combustion chamber. If the gas turbine is increased, it is provided that, with a constant power output, the exhaust-gas temperature increase occurring at the outlet of the gas turbine due to the increase in combustion temperature is at least partially compensated for by the addition of a liquid or vaporous medium.
- Increasing the exhaust gas temperature provides an effective means of reducing CO emissions. So far, however, this measure is limited by the maximum permissible operating temperature of the gas turbine components and the components downstream of the gas turbine outlet.
- a boiler which works as a heat recovery steam generator for a steam turbine downstream of the gas turbine, an exhaust housing of the gas turbine and / or an exhaust gas diffuser of the gas turbine. Since the exhaust gas temperature is lowered by an addition of liquid or vaporous means at or downstream of the exit of the gas turbine, the exhaust gas temperature occurring before the place of addition can be far higher than the maximum permissible operating temperature of the components downstream thereof which contain the exhaust gas to lead.
- the cycle running in the gas turbine is operated with an exhaust gas temperature which is above the operating temperature of the said components, the exhaust gas temperature-limiting components nevertheless carrying an exhaust gas whose temperature is below the maximum permissible operating temperature. Consequently, despite the increased combustion temperature, it is ensured that the components following the gas turbine outlet do not become too hot. This reduces the occurrence of CO emissions in partial load operation or makes it possible to operate the gas turbine in further lowered power ranges without endangering the components.
- the combustion temperature is to be understood as the temperature of the flames which occur in the primary zone of burners. This temperature is also known as the theoretical flame temperature.
- the addition of the vapor or liquid medium does not take place in the flame, but in the flue gas produced by the flame.
- the former is common and has been used very early to control and reduce the NO x emissions of previously common diffusion burners.
- the medium is added immediately after the last turbine stage of the gas turbine or behind the bearing star of the gas turbine, in which the rotor of the gas turbine is usually mounted radially.
- Gas turbine can be increased, can have any value. It is independent of the legally prescribed emission limit value for CO emissions.
- the predetermined limit value for the CO emission according to the invention is selected such that it triggers the start of the method according to the invention in accordance with the desired mode of operation.
- the vaporous medium is process steam of a combined cycle power plant, which does not have to deliver any process steam at very low load delivery, so that it is available for the cooling of the exhaust gas.
- the combustion temperature is raised so far and the added amount of medium selected so that the adjusting after the addition of the medium exhaust gas temperature is about the same size as the exhaust gas temperature at the same place at rated power without the addition of medium would occur or only slightly deviates from this.
- This embodiment is based on the following train of thought:
- the intake mass flow of the compressor is initially reduced by the closing of inlet guide vanes of the compressor.
- the pressure ratio of the gas turbine is reduced and as a result, the exhaust gas temperature increases at a fixed combustion temperature.
- the maximum permissible exhaust gas temperature at the turbine outlet is predetermined by the material temperatures of the gas turbine and also by any downstream boiler (for steam generation). If the exhaust gas reaches this maximum temperature at discharge by means of compressor mass flow reduction, the state of the art must be further reduced as the load is further reduced, as well as the combustion temperature.
- the compressor mass flow which would mean raising the exhaust gas temperature above the maximum permissible material temperature of the components connected downstream of the gas turbine.
- the inadmissibly increased exhaust gas temperature is lowered by the addition of the vapor or liquid medium so far that they are in is approximately equal to the maximum permissible material temperature of the gas turbine components or the gas turbine downstream components.
- gas turbines are designed so that the permissible material temperatures are reached during nominal operation.
- a particular advantage of the invention is that existing gas turbines can be converted relatively easily for the operation of the method according to the invention. Modifications of the gas turbine itself are not necessary, but only their exhaust gas line for feeding a liquid or vapor medium to be trained. Also, there is no loss of efficiency as in the prior art by bypassing Verêtrend Kunststoff. Optionally, even an improvement in efficiency occur because of
- Burnout of the flame is improved.
- the single figure shows schematically a gas turbine with the possibility of supplying a vaporous or liquid medium in the exhaust gas.
- Figure 1 shows schematically a stationary gas turbine 10 with a compressor 12 and a turbine unit 14, the rotors are rigidly coupled together. Between the compressor outlet and the inlet section of the turbine unit 14, a combustion chamber 16 is provided. This can be configured as a silo combustion chamber, tube combustion chamber or as an annular combustion chamber. In the case of tube combustion chambers, the gas turbine 10 usually ten, twelve or more tube combustion chambers.
- the turbine unit 14 comprises a total of four consecutive turbine stages 14 a , 14 b , 14 c , 14 ⁇ ä, which are also shown only schematically in the single figure.
- the compressor 12 draws in ambient air, compresses it and supplies it to the combustion chamber 16. There, the compressed air is mixed with a fuel B and burned in a flame to a hot gas HG.
- the hot gas HG flows into the inlet of the turbine unit 14 and relaxes work on the turbine blades of the turbine unit 14, not shown further.
- the resulting exhaust gas RG flows at the outlet of the turbine unit 14 via an exhaust gas diffuser, not shown. Thereafter, the exhaust gas RG is discharged either via a chimney into the environment, or the exhaust gas RG is fed to a so-called boiler, which uses as a heat recovery steam generator, the heat energy contained in the exhaust gas for the production of steam. The steam generated in the heat recovery steam generator is then used to drive steam turbines, not shown, or as process steam.
- the power to be provided by the gas turbine 10 can be adjusted. If the gas turbine 10 is operated below its rated power and thus provides only a portion of its maximum achievable potential power to the compressor shaft to the generator 11, it is provided that to reduce CO emissions in the combustion chamber 16 adjusting combustion temperature or primary zone temperature is increased by further rotation of the compressor inlet guide vanes 13 at a constant fuel mass flow m B. Since the gas turbine 10 is already in partial load operation and the temperature of the hot gas HG at the turbine inlet is already below the maximum allowable turbine inlet temperature, the combustion temperature can be further increased without the components arranged at the turbine inlet experience an inadmissibly high material temperature, which would have shortened their life.
- a vaporous or liquid medium M is supplied downstream of the penultimate turbine stage 14c of the gas turbine 10 and / or downstream of the last turbine stage 14d of the gas turbine 10, which in the exhaust gas RG adjusting itself by the combustion temperature increase adjusting exhaust gas temperature increase at least partially.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/768,827 US20160010566A1 (en) | 2013-02-22 | 2014-02-06 | Method for operating a gas turbine below its rated power |
JP2015558393A JP2016510098A (ja) | 2013-02-22 | 2014-02-06 | 定格出力以下でのガスタービンの運転法 |
EP14705075.1A EP2943669A1 (de) | 2013-02-22 | 2014-02-06 | Verfahren zum betreiben einer gasturbine unterhalb ihrer nennleistung |
CN201480009833.2A CN105074169A (zh) | 2013-02-22 | 2014-02-06 | 用于使燃气轮机以低于其额定功率操作的方法 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102013202984.5 | 2013-02-22 | ||
DE102013202984.5A DE102013202984A1 (de) | 2013-02-22 | 2013-02-22 | Verfahren zum Betreiben einer Gasturbine unterhalb ihrer Nennleistung |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014128000A1 true WO2014128000A1 (de) | 2014-08-28 |
Family
ID=50115840
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2014/052310 WO2014128000A1 (de) | 2013-02-22 | 2014-02-06 | Verfahren zum betreiben einer gasturbine unterhalb ihrer nennleistung |
Country Status (6)
Country | Link |
---|---|
US (1) | US20160010566A1 (de) |
EP (1) | EP2943669A1 (de) |
JP (1) | JP2016510098A (de) |
CN (1) | CN105074169A (de) |
DE (1) | DE102013202984A1 (de) |
WO (1) | WO2014128000A1 (de) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2910837T3 (es) * | 2018-02-20 | 2022-05-13 | Siemens Energy Global Gmbh & Co Kg | Método para arrancar un motor de turbina de gas de una central eléctrica de ciclo combinado |
US11898502B2 (en) * | 2020-12-21 | 2024-02-13 | General Electric Company | System and methods for improving combustion turbine turndown capability |
CN112627989A (zh) * | 2021-01-08 | 2021-04-09 | 大连欧谱纳透平动力科技有限公司 | 控制小型燃气轮机排气温度和氮氧化物浓度的***及方法 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2403272A (en) * | 2003-06-28 | 2004-12-29 | Rolls Royce Plc | A gas turbine engine having regulated combustion and steam cooled guide vanes |
DE102008044442A1 (de) | 2007-08-24 | 2009-02-26 | General Electric Co. | Systeme und Verfahren zur Erweiterung des Emissionseinhaltungsbereichs bei Gasturbinen |
US20100175387A1 (en) * | 2007-04-05 | 2010-07-15 | Foust Adam M | Cooling of Turbine Components Using Combustor Shell Air |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SG104914A1 (en) * | 1997-06-30 | 2004-07-30 | Hitachi Ltd | Gas turbine |
CN100432395C (zh) * | 1998-10-23 | 2008-11-12 | 株式会社日立制作所 | 燃气轮机发电设备及空气加湿器 |
JP3683521B2 (ja) * | 2001-10-09 | 2005-08-17 | 川崎重工業株式会社 | コージェネレーション装置の運転方法 |
US6782703B2 (en) * | 2002-09-11 | 2004-08-31 | Siemens Westinghouse Power Corporation | Apparatus for starting a combined cycle power plant |
DE10314041A1 (de) * | 2003-03-28 | 2004-12-02 | Alstom Technology Ltd | Verfahren und Vorrichtung zur Anpassung der Parameter des Heissgases eines Heissgaserzeugers mit nachgeschaltetem technologischem Prozess |
US20050235649A1 (en) * | 2004-01-09 | 2005-10-27 | Siemens Westinghouse Power Corporation | Method for operating a gas turbine |
US7269953B2 (en) * | 2004-08-27 | 2007-09-18 | Siemens Power Generation, Inc. | Method of controlling a power generation system |
US8015826B2 (en) * | 2007-04-05 | 2011-09-13 | Siemens Energy, Inc. | Engine brake for part load CO reduction |
US20090205310A1 (en) * | 2008-02-20 | 2009-08-20 | General Electric Company | Power generation system having an exhaust gas attemperating device and system for controlling a temperature of exhaust gases |
WO2009109446A1 (de) * | 2008-03-05 | 2009-09-11 | Alstom Technology Ltd | Verfahren zur regelung einer gasturbine in einem kraftwerk und kraftwerk zur durchführung des verfahrens |
US8677761B2 (en) * | 2009-02-25 | 2014-03-25 | General Electric Company | Systems and methods for engine turn down by controlling extraction air flows |
US8516786B2 (en) * | 2009-08-13 | 2013-08-27 | General Electric Company | System and method for injection of cooling air into exhaust gas flow |
ITMI20101075A1 (it) * | 2010-06-15 | 2011-12-16 | Ansaldo Energia Spa | Metodo per il controllo delle emissioni in una macchina termica, in particolare una turbina a gas, e macchina termica |
US20140174090A1 (en) * | 2012-12-21 | 2014-06-26 | General Electric Company | System for supplying fuel to a combustor |
-
2013
- 2013-02-22 DE DE102013202984.5A patent/DE102013202984A1/de not_active Ceased
-
2014
- 2014-02-06 JP JP2015558393A patent/JP2016510098A/ja active Pending
- 2014-02-06 WO PCT/EP2014/052310 patent/WO2014128000A1/de active Application Filing
- 2014-02-06 US US14/768,827 patent/US20160010566A1/en not_active Abandoned
- 2014-02-06 EP EP14705075.1A patent/EP2943669A1/de not_active Withdrawn
- 2014-02-06 CN CN201480009833.2A patent/CN105074169A/zh active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2403272A (en) * | 2003-06-28 | 2004-12-29 | Rolls Royce Plc | A gas turbine engine having regulated combustion and steam cooled guide vanes |
US20100175387A1 (en) * | 2007-04-05 | 2010-07-15 | Foust Adam M | Cooling of Turbine Components Using Combustor Shell Air |
DE102008044442A1 (de) | 2007-08-24 | 2009-02-26 | General Electric Co. | Systeme und Verfahren zur Erweiterung des Emissionseinhaltungsbereichs bei Gasturbinen |
Also Published As
Publication number | Publication date |
---|---|
US20160010566A1 (en) | 2016-01-14 |
CN105074169A (zh) | 2015-11-18 |
EP2943669A1 (de) | 2015-11-18 |
DE102013202984A1 (de) | 2014-08-28 |
JP2016510098A (ja) | 2016-04-04 |
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