CN101372914A - Systems and methods for extending gas turbine emissions compliance - Google Patents
Systems and methods for extending gas turbine emissions compliance Download PDFInfo
- Publication number
- CN101372914A CN101372914A CN200810210034.8A CN200810210034A CN101372914A CN 101372914 A CN101372914 A CN 101372914A CN 200810210034 A CN200810210034 A CN 200810210034A CN 101372914 A CN101372914 A CN 101372914A
- Authority
- CN
- China
- Prior art keywords
- air
- compressor
- gas turbine
- turbine engine
- engine systems
- 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.)
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Classifications
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- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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- 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
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
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- 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
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- 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
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
- F02C9/52—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by bleeding or by-passing the working fluid
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- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
-
- 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
- F05D2270/082—Purpose of the control system to produce clean exhaust gases with as little NOx as possible
Abstract
The invention relates to a system and a method for extending a gas turbine emission compliance, in particular to a gas turbine system (100) for operation at low loads. The gas turbine system (100) may comprise a plurality of inlet guide vanes (150), a compressor (110), a turbine (140), and an air movement device (155, 175, 180, 210) for maintaining an emission from the gas turbine system (100) below a predetermined level.
Description
Technical field
[0001] the application relates generally to gas turbine, more specifically, relates to the method and system that enlarges gas turbine emissions compliance (emissions compliance) under low load.
Background technique
[0002] because fuel cost constantly rises, the power station that once is designed to mainly to export with full power the gas-firing that moves moves according to the intermittent type principle now.Coal and nuclear energy generally provide most firm power output now.Gas turbine is used for replenishing the difference during the peak demand increasingly extensively.For example, gas turbine can only use by day, shuts down lower night in electricity needs then.
[0003] during load reduction or " low ", gas turbine generally can keep emissions compliance until dropping to about 45 (45%) percent of fixed load output in full.Below the load, index may appear in carbon monoxide (CO) effulent to be increased, and causes system to exceed emissions compliance on the whole at this.In general, emissions compliance requires turbo machine to produce generally less than that guarantee or predetermined combustion with minimal level.This level can change with ambient temperature, system dimension and other variable.
[0004] if gas turbine is because can not keep emissions compliance owing to hang down electricity needs, it just must shut down, and the miscellaneous equipment in the combined type cycle applications also may need to shut down.This equipment can comprise heat recovery steam generator, steam turbine and other device.After shutting down, gas turbine make these once more online meetings of other system not only expensive but also time-consuming.
[0005] such startup requirement may hinder the power station to produce electric power effectively when demand is high.If can during low electricity needs, keep gas turbine online and keep emissions compliance will have great operability advantage to avoid starting time and expense.
[0006] therefore, need a kind of method that during reducing load, enlarges gas turbine emissions compliance.Reduce the load on the gas turbine and keep emissions compliance can make the operator can utilize the chance of these peak demand simultaneously.
Summary of the invention
[0007] therefore, the application provides a kind of gas turbine engine systems with low load operation.The effulent that gas turbine engine systems can comprise a plurality of air-intake guide vanes, compressor, turbo machine and be used to keep gas turbine engine systems is lower than the air movement system of predeterminated level.
[0008] the application has also described a kind of gas turbine with low load operation.Gas turbine can comprise a plurality of air-intake guide vanes, compressor and improve the air recycle system of the temperature of the outlet air stream that leaves compressor.
[0009] the application has also described a kind of gas turbine engine systems with low load operation.Gas turbine engine systems can comprise a plurality of air-intake guide vanes, compressor, turbo machine and the extract system that deflates from compressor.
[0010] after reading over following detailed description in conjunction with several accompanying drawings and claims, these and other feature of the application will become apparent to those skilled in the art.
Description of drawings
[0011] Fig. 1 is the schematic representation of import venting heating arrangement;
[0012] Fig. 2 is the schematic representation of compressor recirculation structure;
[0013] Fig. 3 is the schematic representation of compression extraction air structure;
[0014] Fig. 4 is the schematic representation of compressor air-discharging box structure.
Reference character
100 gas turbines
110 compressors
120 compressor air-discharging casees
130 firing chambers
140 turbo machines
150 air-intake guide vanes
155 imports venting heating arrangement
160 imports venting heating pipe line
170 valves
175 compressor recirculation structures
180 compression extraction air structures
190 compressor cooling lines
200 valves
The 210 compressor air-discharging casees structure of bleeding
220 compressor air-discharging case cooling lines
230 valves
Embodiment
[0015] referring now to accompanying drawing, wherein, in several accompanying drawings, identical reference character is represented identical assembly, and Fig. 1 is the schematic representation of gas turbine engine systems 100.Gas turbine engine systems 100 can comprise compressor 110, firing chamber 130 and the turbo machine 140 that has compressor air-discharging case 120.In general, gas turbine engine systems 100 receives surrounding atmosphere by one group of air-intake guide vane 150.Surrounding atmosphere is compressed by compressor 110 and is transported to firing chamber 130,130 places in the firing chamber, and surrounding atmosphere is used for burning to produce the combustion gas of heat with fuel stream.The combustion gas of heat are transported to turbo machine 140, and at turbo machine 140 places, the combustion gas of heat are inflated to produce mechanical energy via a plurality of blades and rotating shaft.Turbo machine 140 and compressor 110 generally are connected to public rotating shaft, and this public rotating shaft can also be connected to the load of generator or other type.By improving the combustion zone temperature with the formation that suppresses CO (carbon monoxide) and provide flame stability just may enlarge emissions compliance.The meaning of emissions compliance is that the effulent with gas turbine engine systems 100 maintains below the predeterminated level generally.
[0016] first kind of technology relates to the angle of utilizing import venting heating (inlet bleed heat) and reducing air-intake guide vane 150.The minimum angles that reduces air-intake guide vane 150 reduces the central gas stream by gas turbine engine systems 100, thereby has improved the reaction zone temperature in the firing chamber 130.During low, the angle of air-intake guide vane 150 can be reduced, up to reaching minimum angles or delivery temperature thermoisopleth.Can cause infringement in this operation more than temperature levels to components downstream.In reaching these boundaries after any, the minimizing that reduces requirement fuel stream of load.Yet this minimizing can reduce the reaction zone temperature in the firing chamber 130 and can promote the formation of CO.Therefore, to the minimum angles of air-intake guide vane 150 further reduce can allow before may needing to reduce fuel stream, to operate along the delivery temperature thermoisopleth with low load.It is low that these minimum angles can cause improving in ambient temperature range.According to the character of gas turbine 100, can use the angle of about 50 degree of about 30-at this, typical full operation scope extends to about 90 degree from about 40 degree.Can use other angle at this.
[0017] angle of air-intake guide vane 150 is generally allowed and delivery temperature is maintained at thermoisopleth or is maintained under the thermoisopleth.Improve the delivery temperature thermoisopleth and also can allow operating with air-intake guide vane 150 than Low angle.Can improve thermoisopleth by the operating parameter of adjusting gas turbine 100 generally.In addition, by increasing pipe insulation, selecting different materials and change other parts to cause isothermal variation.
[0018] in the embodiment in figure 1, show an import venting heating arrangement 155.This structure comprises import venting heating pipe line 160, and it can be between compressor air-discharging case 120 and air-intake guide vane 150.Import venting heating pipe line 160 is from compressor air-discharging case 120 extracting airs and air is caused the final stage (upstage) of air-intake guide vane 150.Import venting heating pipe line valve 170 can the position thereon.Valve 170 can be conventional design.Recirculation can promote inlet temperature, the minimizing central gas stream of compressor 110 and improve the stall margin from the air of compressor air-discharging case 120, thereby realizes to operate than Low angle for air-intake guide vane 150.
[0019] Fig. 2 shows compressor recirculation structure 175.In this structure 175, import venting heating pipe line 160 is directly connected to compressor 110.Compressor air also can be drawn out of in any level, and then is directed to the level early that needs described air.Therefore, the air from compressor 110 is carried out recirculation can improve the stall margin and can not influence the total efficiency of using import venting heating, because this import venting adds the entire flow path (Fig. 1) of heat affecting compressor 110.The air of recirculation makes it possible to operating than Low angle for air-intake guide vane 150, thereby reduces central gas stream and promote combustion temperature in the firing chamber 130.
[0020] Fig. 3 illustrates the schematic representation of compression extraction air structure 180.This structure 180 can comprise many compressor cooling lines 190.Each had position of compressor cooling line 190 valve 200 thereon.Valve 200 can be a conventional design.Compressor cooling line 190 provides bleeds, walks around firing chamber 130 and cooling turbomachine 140 from compressor 110.This structure 180 has increased the stream of bleeding during low.The stream of bleeding can be redirected in the turbo machine 140 or in the exhaust passage.
[0021] for example, the first compressor cooling line 190 can be from the 13 grade of secondary nozzle that extends to the turbo machine 140 of compressor 110, and the second compressor cooling line 190 is from the 9th grade of three grades of nozzles that extend to the turbo machine 140 of compressor 110.Guiding in the exhaust passage can be in the upstream or the downstream of the delivery temperature measuring position of any kind.Can bleed from arbitrary level of compressor 110.This place can be public bleed position, perhaps can be the disengaging configuration is set especially in order to make air by-pass.The selection of position can be depended on following factor: recirculation efficient, compressor operation, durability and acoustics.Can use existing bleed position.
[0022] Fig. 4 shows the bleed schematic representation of structure 210 of compressor air-discharging case.This structure 210 can comprise compressor air-discharging case cooling line 220, and described compressor air-discharging case cooling line 220 has valve 230 thereon.Valve 230 can be a conventional design.Can from import venting heating pipe line 160 same position used bleed, perhaps can use additional bleeding.Compressor air-discharging box structure 210 can improve the compressor surge border and can increase the reducing of minimum angles of rate of air sucked in required, import venting heating and air-intake guide vane 150.
[0023], can adopt multiple such technology according to the difference of gas turbine 100 general structures.In fact, every kind of method is applicable to improving low performance.To depend on the general arrangement of gas turbine engine systems 100 and relevant combustion technology to method and operation thereof with interactional selection.Especially, the degree of low improvement can be depending on the frame dimensions of gas turbine 100 and the specific combustion technology of use.
[0024] for example, in having the 7FA+e gas turbine of doing low Nox2.6 combustion system (dry-low-Nox 2.6combustion system), preferred construction can comprise the minimum angles that reduces air-intake guide vane 150, extraction flow is doubled and increase from compressor air-discharging case 120 bleed so that the additive air bypass to venting gas appliance.Can be from General ElectricCompany, Schenectady, New York obtains the 7FA+e gas turbine.For 9FB gas turbine, may need only to reduce the minimum angles of air-intake guide vane 150 and thermoisopleth is improved with similar combustion system.The 9FB gas turbine also can be from General Electric Company, Schenectady, and New York obtains.Also can use the gas turbine of other type at this.Adopt these diverse ways can keep emissions compliance until dropping to about 30 (30%) percent of load.Other improvement also is possible.
Should be understood that [0025] aforementioned content only relates to the application's preferred embodiment, and under the situation of overall spirit of the present invention that does not break away from the qualification of claims and equivalent thereof and scope, those skilled in the art can make multiple changes and improvements.
Claims (10)
1. gas turbine engine systems (100) with low load operation comprising:
A plurality of air-intake guide vanes (150);
Compressor (110);
Turbo machine (140); With
The effulent that is used to keep described gas turbine engine systems (100) is lower than the air movement device (155,175,180,210) of predeterminated level.
2. gas turbine engine systems according to claim 1 (100) is characterized in that: described air movement device (155,175,180,210) comprises the import venting heating pipe line (160) that extends to the upstream of described a plurality of air-intake guide vane (150) from described compressor (110).
3. gas turbine engine systems according to claim 1 (100), it is characterized in that: described compressor (110) comprises compressor air-discharging case (120), and air re-circulation device (155,175,180,210) comprises the import venting heating pipe line (160) that extends to the upstream of described a plurality of air-intake guide vane (150) from described compressor air-discharging case (120).
4. gas turbine engine systems according to claim 1 (100), it is characterized in that: described compressor (110) comprises a plurality of levels, and described air movement device (155,175,180,210) comprises the compressor recirculating line (160) that extends to the compressor stage of upstream from the compressor stage in downstream.
5. gas turbine engine systems according to claim 1 (100) is characterized in that: described air movement device (155,175,180,210) comprises the compressor cooling line (190) that extends to described turbo machine (140) from described compressor (110).
6. gas turbine engine systems according to claim 1 (100) is characterized in that: described air movement device (155,175,180,210) comprises the exhaust pipe (190) that extends to the downstream of described turbo machine (140) from described compressor (110).
7. gas turbine engine systems according to claim 1 (100), it is characterized in that: described compressor (110) comprises compressor air-discharging case (120), and air extractor (155,175,180,210) comprises the exhaust pipe (190) that extends to the downstream of described turbo machine (140) from described compressor air-discharging case (120).
8. gas turbine engine systems according to claim 1 (100) is characterized in that: the load on the described gas turbine engine systems (100) is low to moderate about 30 (30%) percent.
9. gas turbine (100) with low load operation comprising:
A plurality of air-intake guide vanes (150);
Compressor (110); With
Improve the air re-circulation device (175) of the temperature of the outlet air stream that leaves described compressor (110).
10. gas turbine engine systems (100) with low load operation comprising:
A plurality of air-intake guide vanes (150);
Compressor (110);
Turbo machine (140); With
The air extractor (180) that deflates from described compressor.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/844,479 US20090053036A1 (en) | 2007-08-24 | 2007-08-24 | Systems and Methods for Extending Gas Turbine Emissions Compliance |
| US11/844479 | 2007-08-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101372914A true CN101372914A (en) | 2009-02-25 |
Family
ID=40280470
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810210034.8A Pending CN101372914A (en) | 2007-08-24 | 2008-08-22 | Systems and methods for extending gas turbine emissions compliance |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20090053036A1 (en) |
| JP (1) | JP2009052548A (en) |
| CN (1) | CN101372914A (en) |
| CH (1) | CH697810B8 (en) |
| DE (1) | DE102008044442A1 (en) |
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| CN105074170A (en) * | 2013-02-22 | 2015-11-18 | 西门子公司 | Method for operating a gas turbine below the nominal power thereof |
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| JP5566683B2 (en) * | 2009-12-25 | 2014-08-06 | 三菱重工業株式会社 | gas turbine |
| IT1399723B1 (en) * | 2010-04-30 | 2013-05-03 | Nuovo Pignone Spa | METHOD AND SYSTEM FOR THE DETECTION OF LOCKED NOZZLE AND REMEDY |
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| EP2407652A1 (en) | 2010-07-15 | 2012-01-18 | Siemens Aktiengesellschaft | Gas turbine with a secondary air system and method for operating such a gas turbine |
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| RU2623336C2 (en) | 2012-03-30 | 2017-06-23 | АНСАЛДО ЭНЕРДЖИА АйПи ЮКей ЛИМИТЕД | Gas turbine with adjustable air cooling system |
| US9435219B2 (en) | 2012-04-24 | 2016-09-06 | General Electric Company | Gas turbine inlet system and method |
| RU2563445C2 (en) * | 2012-07-13 | 2015-09-20 | Альстом Текнолоджи Лтд | Method and device to regulate surging of gas turbine engine |
| WO2014009524A1 (en) * | 2012-07-13 | 2014-01-16 | Alstom Technology Ltd | Gas turbine power plant with flue gas recirculation |
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| BR112015014656A2 (en) | 2012-12-21 | 2017-07-11 | Siemens Ag | method for operating a gas turbine combustor |
| EP2789828A1 (en) * | 2013-04-12 | 2014-10-15 | Siemens Aktiengesellschaft | Method for controlling the CO emissions of a gas turbine |
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| EP2896793A1 (en) * | 2014-01-21 | 2015-07-22 | Alstom Technology Ltd | Method of operating a gas turbine assembly and the gas turbine assembly |
| EP2907990A1 (en) * | 2014-02-18 | 2015-08-19 | Siemens Aktiengesellschaft | Method for operating a gas turbine installation, and the same |
| US20170058784A1 (en) * | 2015-08-27 | 2017-03-02 | General Electric Company | System and method for maintaining emissions compliance while operating a gas turbine at turndown condition |
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| JP7337005B2 (en) | 2020-02-26 | 2023-09-01 | 三菱重工業株式会社 | gas turbine plant |
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2007
- 2007-08-24 US US11/844,479 patent/US20090053036A1/en not_active Abandoned
-
2008
- 2008-08-18 DE DE102008044442A patent/DE102008044442A1/en not_active Withdrawn
- 2008-08-20 JP JP2008211278A patent/JP2009052548A/en active Pending
- 2008-08-21 CH CH01329/08A patent/CH697810B8/en not_active IP Right Cessation
- 2008-08-22 CN CN200810210034.8A patent/CN101372914A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105074169A (en) * | 2013-02-22 | 2015-11-18 | 西门子股份公司 | Method for operating a gas turbine below its rated power |
| CN105074170A (en) * | 2013-02-22 | 2015-11-18 | 西门子公司 | Method for operating a gas turbine below the nominal power thereof |
| CN105074170B (en) * | 2013-02-22 | 2017-04-05 | 西门子公司 | For the method that gas turbine is run below its rated power |
| US10408135B2 (en) | 2013-02-22 | 2019-09-10 | Siemens Aktiengesellschaft | Method for operating a gas turbine below the nominal power thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2009052548A (en) | 2009-03-12 |
| US20090053036A1 (en) | 2009-02-26 |
| DE102008044442A1 (en) | 2009-02-26 |
| CH697810B8 (en) | 2013-02-28 |
| CH697810B1 (en) | 2012-06-15 |
| CH697810A2 (en) | 2009-02-27 |
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