EP0276397A1 - Chambre de combustion pour turbine à gaz - Google Patents
Chambre de combustion pour turbine à gaz Download PDFInfo
- Publication number
- EP0276397A1 EP0276397A1 EP87117059A EP87117059A EP0276397A1 EP 0276397 A1 EP0276397 A1 EP 0276397A1 EP 87117059 A EP87117059 A EP 87117059A EP 87117059 A EP87117059 A EP 87117059A EP 0276397 A1 EP0276397 A1 EP 0276397A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- afterburner
- primary
- combustion
- central
- 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.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
- F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
- F23C6/042—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with fuel supply in stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
- F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
- F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
- F23C6/047—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure with fuel supply in stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
Definitions
- the present invention relates to a combustion chamber of gas turbines for operation with liquid fuels. It also relates to a method for operating such a combustion chamber.
- the low NO x emission values still tolerated by law can only be maintained in the case of a planar combustion if the residence time of the gas particles in hot oxygen-rich zones is as short as possible, namely not more than a few milliseconds.
- the temperature in the reaction area must not fall below a certain limit.
- This grading can mean either a sub-stoichiometric primary combustion zone with subsequent post-combustion at low temperatures or the stepwise connection of over-stoichiometric burner elements. In any case, the grading also requires a powerful mixing mechanism.
- premix combustion has proven to be the technically best measure for NO x reduction for the combustion of gaseous fuels.
- a premix combustion can consist, for example, of a premix process with a large air ratio taking place within a number of tubular elements between the fuel and the compressor air before the actual combustion process takes place downstream of a flame holder.
- the emission values of pollutants from combustion can be significantly reduced.
- Combustion with the largest possible air ratio - given that the flame is still burning and then that not too much CO is produced - not only reduces the amount of NO X pollutants, but also causes a consistent reduction in other pollutants, namely, as already mentioned, CO and unburned hydrocarbons.
- this optimization process can be driven, with regard to lower NO x emission values, in such a way that the space for combustion and after-reaction is kept much longer than would be necessary for the actual combustion.
- the invention is based on the object, in a combustion chamber of the type mentioned, having comparable low NO x emission values as in combustion chambers operated with gaseous fuels to achieve without the risk of self-ignition of the liquid fuels outside the combustion chamber.
- the advantage of the invention is to be seen essentially in the fact that a system is provided in a simple manner that generates low NO x emissions, this system being able to achieve the premixing without the technology and infrastructure which are per se quite complex.
- the basic idea is to provide a primary burner and afterburner system.
- the liquid fuel is injected directly into the combustion chamber.
- the injected fuel is shielded with an air jacket, which is a non-self-sufficient burner.
- the afterburner which is placed in a central chamber at the end of the primary burner chamber, is used in combination with one or more primary burners.
- the hot gases generated by the primary burners should not be able to ignite the mixture generated by the afterburner in the immediate vicinity of the fuel nozzle of the afterburner, in order to avoid combustion under near-stoichiometric conditions. This is ensured by the shielding air jacket, which is not swirled and which initially effectively shields the fuel mist emanating from the afterburner nozzle against the external hot gases.
- Fig. 1 shows a combustion chamber for gas turbines, which is housed in the GT ring housing 1. If the entire combustion chamber is embedded in a GT ring housing 1, it is connected to the compressed air 11 from the compressor 10 like a chamber.
- the gas turbine ring casing wall is designed to withstand the compressor end pressure.
- the geometric shape of the combustion chamber, as the axial section 12 wants to symbolize, is cylindrical and consists of two primary combustion chambers 5, 5a arranged at the ends, which are arranged symmetrically and V-shaped with respect to the central combustion chamber 6. Of course, the primary combustion chambers 5, 5a can lie in a horizontal plane with respect to the central axis of the central combustion chamber 6.
- the primary combustion chambers 5, 5a themselves are equipped at their front ends in the circumferential direction with a number of axially parallel primary burners 2, 2a which depend on the performance of the combustion chamber. These essentially consist of a fuel line 3, 3a and a swirl body 8, 8a. Instead of a continuous circular cylindrical primary combustion chamber 5, 5a, several self-contained combustion chamber units can be provided distributed over the circumference, each consisting of a pair of twin burners with preferably twist bodies oriented in opposite directions. This has the effect that an effective mixing process can be generated in the individual combustion chamber units, an annular cylindrical outlet channel collecting the hot gases emerging from the individual combustion chamber units in order to then lead them to the central combustion chamber 6.
- one after burner 4 is provided in each case. From the afterburner 4, liquid fuel 15 is fed directly into the combustion chamber and shielded with an air jacket 14.
- the afterburner 4 is designed in such a way that it is not self-sufficient, ie its ignition requires a permanent ignition.
- the hot gases 13 generated by the primary burners 2, 2a should not be able to ignite the mixture 14/15 produced by the afterburner 4 in the immediate vicinity of the fuel nozzle of the afterburner 4.
- the shielding air jacket 14 which should preferably be untwisted and initially effectively shields the fuel mist 15 emanating from the afterburner nozzle against the hot gases 13 of the primary burners 2, 2a arriving there.
- An ignition of the afterburner mixture 14/15 should only be possible when the liquid fuel 15 introduced by the burner nozzle has mixed sufficiently with the shielding air jacket 14.
- the air ratio related to the fuel supply of the afterburner 4 and the air jacket 14 is determined according to the same criteria as for a premix burner.
- the rapid intermixing of the hot gases 13 plays after it is the first foreign ignition of the afterburner mixture 14/15 have played an important role in the stability of the combustion, which is why it must be ensured that the pulse density ratio between primary burner gases 13 and afterburner mixture 14/15 is chosen to be very high - well over 1. It is confirmed that an optimally inserted afterburner 4 hardly produces NO X as a premix burner, while the primary burner 2, 2a, which must of course be self-sustaining, for example, designed as a diffusion burner, causing significantly higher NO x emissions. For this reason, in a gas turbine combustion chamber, provision must be made to supply the highest possible proportion of the liquid fuel via the afterburner 4.
- the primary burners 2, 2a should therefore be planned as small as possible and they should be operated with high air ratios: both measures make it possible to keep the NO x emissions from the operation of the primary burners 2, 2a as low as possible. Consequently, for the operation of a gas turbine combustion chamber, this means that the primary burners 2, 2a and the afterburner 4 are operated in stages.
- the afterburner 4 is preferably switched on at a load point near zero load of the gas turbines. Between the switch-on point and the maximum load, the load is regulated only via the fuel supply to the afterburner 4, it being possible for a gradual reduction in the fuel supply to the primary burner 2, 2a to be initiated as the afterburner load increases.
- the lower limit for the reduction of the fuel supply to the primary burners 2, 2a is given on the one hand by the extinguishing limit of the primary burner and on the other hand by the necessity that the temperature of the exhaust gas of the primary burner must be high enough to initiate the burnout of the afterburner fuel.
- the air jacket 14 shields the afterburner 4 and its liquid fuel spray cone 15 from the incoming hot gases 13 from the primary burners 2, 2a. As already explained, the mixture 14/15 produced by the afterburner 4 should not come to ignition in the immediate vicinity of the fuel nozzle 15 under near-stoichiometric conditions.
- the length of the mixing chamber 7 is heavily dependent on the strength of the mixing process: observations have shown that a vortex-free flow with a uniform pressure is achieved well after a length of about three diameters of the corresponding combustion chamber unit.
- the optimal design of the primary burners 2, 2a reference is made to the description according to EP-0 193 029, in particular under FIG. 2.
- the solution shown in FIG. 2 wants to further protect the afterburner 4 from the incoming hot gases 13 of the primary burners 2, 2a.
- the inlet 16 of the shielding air 14 into the combustion chamber is extended at least so that the liquid fuel spray cone 15 is also shielded.
- the hot gases 13 only flow further downstream to the afterburner mixture 14/15; there the mixing of the liquid fuel 15 with the shielding jacket air 14 has progressed to such an extent that ignition of this mixture 14/15 can take place.
- FIG 3 shows a further variant of how the afterburner 4 and its liquid fuel spray cone 15 can be shielded from the incoming hot gases 13 in the area of the central combustion chamber 6.
- the shielding air 14 flows on the one hand along the afterburner 4 and on the other hand laterally between a plurality of fins 17 into the central combustion chamber 6.
- Such a provision offers the advantage that the mixture between the liquid fuel 15 and the shielding mixture Air 14 is optimized in front of the mixing chamber 7. At the beginning of the mixing chamber 7, this mixture 14/15 is then ignited by the hot gases 13 flowing there. The entire length of the mixing chamber 7 thus remains available in order to provide a vortex-free flow with a uniform pressure and temperature profile for the turbine to be acted upon.
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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH4892/86A CH672366A5 (fr) | 1986-12-09 | 1986-12-09 | |
CH4892/86 | 1986-12-09 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0276397A1 true EP0276397A1 (fr) | 1988-08-03 |
EP0276397B1 EP0276397B1 (fr) | 1991-01-30 |
Family
ID=4284343
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP87117059A Expired - Lifetime EP0276397B1 (fr) | 1986-12-09 | 1987-11-19 | Chambre de combustion pour turbine à gaz |
Country Status (5)
Country | Link |
---|---|
US (1) | US4805411A (fr) |
EP (1) | EP0276397B1 (fr) |
JP (1) | JPS63156926A (fr) |
CH (1) | CH672366A5 (fr) |
DE (1) | DE3767873D1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1998021527A1 (fr) * | 1996-11-08 | 1998-05-22 | European Gas Turbines Limited | Dispositif combusteur |
EP2532857A1 (fr) * | 2011-06-06 | 2012-12-12 | United Technologies Corporation | Agencement de turbomachine avec chambres de combustion ayant différentes directions de flux et procédé d'exploitation associé |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4928481A (en) * | 1988-07-13 | 1990-05-29 | Prutech Ii | Staged low NOx premix gas turbine combustor |
US5199265A (en) * | 1991-04-03 | 1993-04-06 | General Electric Company | Two stage (premixed/diffusion) gas only secondary fuel nozzle |
US5259184A (en) * | 1992-03-30 | 1993-11-09 | General Electric Company | Dry low NOx single stage dual mode combustor construction for a gas turbine |
US5323604A (en) * | 1992-11-16 | 1994-06-28 | General Electric Company | Triple annular combustor for gas turbine engine |
DE19615910B4 (de) * | 1996-04-22 | 2006-09-14 | Alstom | Brenneranordnung |
DE59808754D1 (de) * | 1997-12-19 | 2003-07-24 | Mtu Aero Engines Gmbh | Vormischbrennkammer für eine Gasturbine |
US6430919B1 (en) * | 2000-03-02 | 2002-08-13 | Direct Propulsion Devices, Inc. | Shaped charged engine |
AU2002347186A1 (en) * | 2002-01-14 | 2003-07-24 | Alstom Technology Ltd | Burner arrangement for the annular combustion chamber of a gas turbine |
US8387390B2 (en) | 2006-01-03 | 2013-03-05 | General Electric Company | Gas turbine combustor having counterflow injection mechanism |
US8178045B2 (en) * | 2007-12-17 | 2012-05-15 | University Of Louisville Research Foundation, Inc. | Interchangeable preconcentrator connector assembly |
US8448532B2 (en) * | 2009-03-18 | 2013-05-28 | The United States Of America As Represented By The Secretary Of The Navy | Actively cooled vapor preconcentrator |
RU2534189C2 (ru) * | 2010-02-16 | 2014-11-27 | Дженерал Электрик Компани | Камера сгорания для газовой турбины(варианты) и способ эксплуатации газовой турбины |
US20230280035A1 (en) * | 2022-03-07 | 2023-09-07 | General Electric Company | Bimodal combustion system |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2412120A1 (de) * | 1973-03-13 | 1974-09-19 | Snecma | Umweltfreundliche brennkammer fuer gasturbinen |
US4012904A (en) * | 1975-07-17 | 1977-03-22 | Chrysler Corporation | Gas turbine burner |
US4052844A (en) * | 1975-06-02 | 1977-10-11 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Gas turbine combustion chambers |
GB2010407A (en) * | 1977-12-01 | 1979-06-27 | United Technologies Corp | Burner for gas turbine engine |
GB2013788A (en) * | 1978-01-28 | 1979-08-15 | Rolls Royce | Gas turbine engine combustion equipment |
US4292801A (en) * | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
GB2072827A (en) * | 1980-03-29 | 1981-10-07 | Rolls Royce | A tubo-annular combustion chamber |
GB2073400A (en) * | 1980-04-02 | 1981-10-14 | United Technologies Corp | Fuel injector |
DE3217674A1 (de) * | 1981-05-12 | 1982-12-02 | Hitachi, Ltd., Tokyo | Combustor fuer eine gasturbine |
GB2146425A (en) * | 1983-09-08 | 1985-04-17 | Hitachi Ltd | Method of supplying fuel into gas turbine combustor |
EP0169431A1 (fr) * | 1984-07-10 | 1986-01-29 | Hitachi, Ltd. | Chambre de combustion pour turbine à gaz |
EP0193029A1 (fr) * | 1985-02-26 | 1986-09-03 | BBC Brown Boveri AG | Chambre de combustion pour turbines à gaz |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3872664A (en) * | 1973-10-15 | 1975-03-25 | United Aircraft Corp | Swirl combustor with vortex burning and mixing |
US4173118A (en) * | 1974-08-27 | 1979-11-06 | Mitsubishi Jukogyo Kabushiki Kaisha | Fuel combustion apparatus employing staged combustion |
US4249373A (en) * | 1978-01-28 | 1981-02-10 | Rolls-Royce Ltd. | Gas turbine engine |
GB2043868B (en) * | 1979-03-08 | 1982-12-15 | Rolls Royce | Gas turbine |
JPS5755975U (fr) * | 1980-09-16 | 1982-04-01 | ||
JPS59202324A (ja) * | 1983-05-04 | 1984-11-16 | Hitachi Ltd | ガスタ−ビン低NOx燃焼器 |
-
1986
- 1986-12-09 CH CH4892/86A patent/CH672366A5/de not_active IP Right Cessation
-
1987
- 1987-11-19 DE DE8787117059T patent/DE3767873D1/de not_active Expired - Fee Related
- 1987-11-19 EP EP87117059A patent/EP0276397B1/fr not_active Expired - Lifetime
- 1987-11-25 US US07/125,126 patent/US4805411A/en not_active Expired - Fee Related
- 1987-12-09 JP JP62309765A patent/JPS63156926A/ja active Pending
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2412120A1 (de) * | 1973-03-13 | 1974-09-19 | Snecma | Umweltfreundliche brennkammer fuer gasturbinen |
US4052844A (en) * | 1975-06-02 | 1977-10-11 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Gas turbine combustion chambers |
US4012904A (en) * | 1975-07-17 | 1977-03-22 | Chrysler Corporation | Gas turbine burner |
GB2010407A (en) * | 1977-12-01 | 1979-06-27 | United Technologies Corp | Burner for gas turbine engine |
GB2013788A (en) * | 1978-01-28 | 1979-08-15 | Rolls Royce | Gas turbine engine combustion equipment |
US4292801A (en) * | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
GB2072827A (en) * | 1980-03-29 | 1981-10-07 | Rolls Royce | A tubo-annular combustion chamber |
GB2073400A (en) * | 1980-04-02 | 1981-10-14 | United Technologies Corp | Fuel injector |
DE3217674A1 (de) * | 1981-05-12 | 1982-12-02 | Hitachi, Ltd., Tokyo | Combustor fuer eine gasturbine |
GB2146425A (en) * | 1983-09-08 | 1985-04-17 | Hitachi Ltd | Method of supplying fuel into gas turbine combustor |
EP0169431A1 (fr) * | 1984-07-10 | 1986-01-29 | Hitachi, Ltd. | Chambre de combustion pour turbine à gaz |
EP0193029A1 (fr) * | 1985-02-26 | 1986-09-03 | BBC Brown Boveri AG | Chambre de combustion pour turbines à gaz |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1998021527A1 (fr) * | 1996-11-08 | 1998-05-22 | European Gas Turbines Limited | Dispositif combusteur |
US6360525B1 (en) | 1996-11-08 | 2002-03-26 | Alstom Gas Turbines Ltd. | Combustor arrangement |
EP2532857A1 (fr) * | 2011-06-06 | 2012-12-12 | United Technologies Corporation | Agencement de turbomachine avec chambres de combustion ayant différentes directions de flux et procédé d'exploitation associé |
Also Published As
Publication number | Publication date |
---|---|
EP0276397B1 (fr) | 1991-01-30 |
CH672366A5 (fr) | 1989-11-15 |
US4805411A (en) | 1989-02-21 |
DE3767873D1 (de) | 1991-03-07 |
JPS63156926A (ja) | 1988-06-30 |
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