EP0713058B1 - Brennkammer mit Mehrstufenverbrennung - Google Patents
Brennkammer mit Mehrstufenverbrennung Download PDFInfo
- Publication number
- EP0713058B1 EP0713058B1 EP95810698A EP95810698A EP0713058B1 EP 0713058 B1 EP0713058 B1 EP 0713058B1 EP 95810698 A EP95810698 A EP 95810698A EP 95810698 A EP95810698 A EP 95810698A EP 0713058 B1 EP0713058 B1 EP 0713058B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- combustion
- space
- burner
- fuel
- 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.)
- Expired - Lifetime
Links
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
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/02—Disposition of air supply not passing through burner
- F23C7/06—Disposition of air supply not passing through burner for heating the incoming air
-
- 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
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
Definitions
- the invention relates to a method for operating a multi-stage Combustion chamber, with at least one primary burner Premix type, in which within a premixing room the Fuel injected via nozzles prior to ignition is intensively mixed with primary combustion air, and with at least an afterburner, downstream of the pre-combustor is arranged and introduced into the secondary combustion air becomes. It also relates to a combustion chamber for implementation of the procedure.
- Such a two-stage combustion chamber and a method for its operation is known from DE-C2 31 49 581.
- Vortex cups with central fuel injection nozzles are used there as primary burners of the premix type.
- the combustion chamber is a so-called "rich / lean two-stage combustion chamber", the gases having a fuel / air equivalence ratio in the first combustion stage which is greater than 1.
- the gases In the second combustion stage, the gases have a fuel / air equivalence ratio that is less than 1.
- the transition from the rich to the lean mixture can be realized as quickly as possible.
- the mixture is therefore accelerated and the secondary combustion air is injected into the accelerated mixture.
- the purpose of the acceleration is to keep the duration of the mixture in the zone in which the fuel / air equivalence ratio is 1 as short as possible. This is because the formation rate of NO X is greatest at this medium ratio.
- the object of the invention is to create a "lean / lean" process and the associated combustion chamber using such modern premix burners, with which extremely low NO x emissions are achieved.
- a combustion chamber for carrying out this method draws arranged from one at the head end of the combustion chamber Double-cone burner of the premix type, with a subsequent one Pre-combustion chamber, by one following the pre-combustion chamber Acceleration path for the flue gas, which in one Afterburner opens, and through air inlets in the area of the acceleration section in the double wall Combustion chamber boundary are arranged, as well as by at the entrance of the afterburner arranged injection means for Additional fuel.
- the advantage of the invention can be seen in particular in the fact that the premix burner can be operated at the lower extinguishing limit, with only about 9 ppm NO x initially being produced;
- the self-igniting afterburning process delivers gases with the desired high temperature of 1800K (approx. 1530 ° C), which gases only have NO x values below 6 ppm due to the supply of additional air and due to the short residence times.
- Fig. 1 50 is a jacketed plenum, which is usually the one not shown Compressor-fed combustion air and one for example, supplies annular combustion chamber 60.
- This The combustion chamber has two stages and essentially exists a pre-combustion chamber 61 and a downstream one located post-combustion chamber 62, both with a combustion chamber wall 63 are covered. Of all the combustion air part a of the pre-combustion chamber 61 is fed directly, while parts b and c initially have cooling functions exercise.
- annular dome 55 On the pre-combustion chamber 61, which is at the head end of the combustion chamber 60 is located and its combustion chamber through a front panel 54 is limited, an annular dome 55 is placed.
- a burner 110 is arranged in this dome in such a way that the burner outlet is at least approximately flush with the Front plate 54.
- the longitudinal axis 51 of the primary burner 110 runs coaxially to the longitudinal axis 52 of the combustion chamber 60 a number of such burners are distributed around the circumference 110 side by side on the annular front plate 52 arranged.
- the fuel will fed to the burner via a fuel lance 120 which penetrates the cathedral and plenum walls.
- Double cone burner such as from EP-B1-0 321 809 is known. Essentially it consists of two hollow, conical part-bodies 111, 112, which are nested in the direction of flow.
- the respective central axes 113, 114 of the two Partial body offset from each other.
- the neighboring walls of the two partial bodies form in their longitudinal extent tangential slots 119 for the combustion air that on this way gets into the interior of the burner.
- the fuel is injected into the at an acute angle Hollow cone injected.
- the resulting tapered fuel profile is from the tangentially flowing combustion air enclosed.
- the concentration of the Fuel continuously as a result of mixing with the Combustion air reduced.
- the burner can also be operated with gaseous fuel.
- Gas inflow openings 117 are provided in the area of the tangential slots 119 in the Walls of the two partial bodies distributed in the longitudinal direction.
- the premix burner is operated with approx. 56% of the total available combustion air and that close to the lower extinguishing limit; ie the corresponding amount of fuel is set so that a temperature of 1640K (approx. 1370 ° C.) and a NO x content of 9 ppm prevail in the combustion chamber 61.
- Such fuel lances are at the entrance to the afterburning chamber 62 121 arranged. In the case of an annular combustion chamber several such lances are distributed over the circumference. Out the additional fuel is supplied to them - evenly over the Flow cross section distributed - injected into the main flow.
- the remaining ones are upstream of this fuel injection 44% air is appropriately mixed into the combustion process.
- This is the air that initially is used to cool the combustion chamber walls.
- These combustion chamber walls are both in the area of the pre-combustion chamber 61 and in the area of the afterburner 62 double-walled.
- the inner wall 63a is in the Plane of the intended air supply with inlet openings 64 see.
- the amount of air that is added to the main flow is composed of two partial flows.
- the cooling air b of the pre-combustion chamber which is approximately 16% of the total and the cooling air c of the afterburner, which makes up about 28% of the total.
- the pressure drop is the air via the wall cooling approx. 4%, that via the Mixture of combustion gases and cooling air approx. 2%.
- the mixing temperature after admixing the cooling air to the combustion gases in the pre-combustion chamber is approximately 980 ° C., so that the fuel / air mixture present at the inlet into the afterburning chamber 62 is self-igniting.
- the amount of additional fuel is selected so that the desired final temperature of 1700 K (approx. 1430 ° C.) prevails in the afterburning chamber 62.
- the NO x content of 9 ppm resulting from the pre-combustion is reduced to less than 6 ppm by the dilution.
- afterburning chamber 62 is in its axial Extension is dimensioned so that it is complete Burnout takes place.
- FIG. 2 schematically shows a five-stage combustion chamber which can be operated as follows: Fuel is fed to the premix burner 110 via the fuel lance 120 and burned with approximately 10% of the combustion air a. The amount of fuel supplied via the lance 120 is adjusted so that a temperature of 1640 K (approx. 1370 ° C.) and a NO x content of 9 ppm prevail in the combustion chamber A. The mixture is accelerated; A further 8% of air, in this case wall cooling air, is introduced in level b, and a corresponding amount of fuel is introduced via fuel lances 121, so that a temperature of 1500 K (approx. 1230 ° C.) prevails in combustion chamber B.
- a further 14% of air is introduced in level c and a corresponding amount of fuel is introduced via fuel lances 130, so that a temperature of 1500 K (approx. 1230 ° C.) also prevails in combustion chamber C.
- a further 26% of air is introduced in level d and a corresponding amount of fuel is introduced via fuel lances 131, so that a temperature of 1500K (approx. 1230 ° C.) also prevails in combustion chamber D.
- the remaining 42% air is introduced in level e and the remaining amount of fuel is introduced via fuel lances 132, so that the desired final temperature of 1700 K (approx. 1430 ° C.) prevails in combustion chamber E.
- the NO x content in the combustion chamber E is only 3 ppm.
- the optimal number of combustion stages with regard to the NO x value to be achieved is to be selected as a function of the pressure loss to be accepted and the combustion chamber length.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Combustion Of Fluid Fuel (AREA)
- Regulation And Control Of Combustion (AREA)
Description
- dass der Primärbrenner ein flammenstabilisierender Vormischbrenner ist, welcher an der unteren Stabilitätsgrenze betrieben wird,
- dass zwischen Vorbrennraum und Nachbrennraum das Rauchgas beschleunigt wird,
- und dass in die den Vorbrennraum verlassende Rauchgasströmung zwecks Bildung eines selbstzündenden Gemisches Kühlluft aus der doppelwandigen Brennkammerbegrenzung und Zusatzbrennstoff eingeführt wird.
- Fig. 1
- einen Teillängsschnitt einer ersten zweistufigen Brennkammer;
- Fig. 2
- einen Teillängsschnitt einer zweiten fünf stufigen Brennkammer;
- Fig. 3A
- einen Querschnitt durch einen Vormischbrenner der Doppelkegel-Bauart im Bereich seines Austritts;
- Fig. 3B
- einen Querschnitt durch denselben Vormischbrenner im Bereich der Kegelspitze;
Über die Brenstofflanze 120 wird Brennstoff dem Vormischbrenner 110 zugeleitet und mit ca. 10% der Verbrennungsluft a verbrannt. Die über die Lanze 120 zugeführte Brennstoffmenge wird dabei so eingestellt, dass im Brennraum A eine Temperatur von 1640K (ca. 1370°C) und ein NOX-Gehalt von 9 ppm vorherrscht. Das Gemisch wird beschleunigt; in der Ebene b werden weitere 8% Luft, in diesem Fall Wand-Kühlluft, und über die Brennstofflanzen 121 eine entsprechende Menge Brennstoff eingeführt, so dass im Brennraum B eine Temperatur von 1500K (ca. 1230°C) herrscht. In der Ebene c werden weitere 14% Luft und über die Brennstofflanzen 130 eine entsprechende Menge Brennstoff eingeführt, so dass im Brennraum C ebenfalls eine Temperatur von 1500K (ca. 1230°C) herrscht. In der Ebene d werden weitere 26% Luft und über die Brennstofflanzen 131 eine entsprechende Menge Brennstoff eingeführt, so dass auch im Brennraum D eine Temperatur von 1500K (ca. 1230°C) herrscht. In der Ebene e werden die restlichen 42% Luft und über die Brennstofflanzen 132 die restliche Menge Brennstoff eingeführt, so dass im Brennraum E die gewünschte Endtemperatur von 1700K (ca. 1430°C) herrscht. Durch die sukksessive Reduzierung des anlässlich der Vorverbrennung entstandenen NOX ist es durchaus möglich, dass im Brennraum E nur noch ein NOX-Gehalt von 3 ppm vorliegt.
Claims (3)
- Verfahren zum Betrieb einer mehrstufigen Brennkammer, mit mindestens einem Primärbrenner (110) der Vormischbauart, bei dem innerhalb eines Vormischraumes der über Düsen eingespritzte Brennstoff vorgängig der Zündung mit Primärbrennluft intensiv vermischt wird, und mit mindestens einem Nachbrennraum (62, B, C, D, E), der stromabwärts des Vorbrennraumes (61, A) angeordnet ist, und in den Sekundärbrennluft eingeleitet wird dadurch gekennzeichnet,dass der Primärbrenner (110) ein flammenstabilisierender Vormischbrenner ist, welcher an der unteren Stabilitätsgrenze betrieben wird,dass zwischen Vorbrennraum (61, A) und Nachbrennraum (62, B, C, D, E) das Rauchgas beschleunigt wird,und dass in die den Vorbrennraum verlassende Rauchgasströmung zwecks Bildung eines selbstzündenden Gemisches Kühlluft aus der doppelwandigen Brennkammerbegrenzung und Zusatzbrennstoff eingeführt wird.
- Brennkammer zur Durchführung des Verfahrens nach Anspruch 1, wobeiam Kopfende der Brennkammer ein Vormischbrenner (110) angeordnet ist, mit anschliessendem Vorbrennraum (61, A),dass eine dem Vorbrennraum folgende Beschleunigungsstrecke (70) für das Rauchgas vorgesehen ist, welche in einen Nachbrennraum (62, B, C, D, E) mündet,dass im Bereich der Beschleunigungsstrecke (70) Einströmöffnungen (64) in der doppelwandigen Brennkammerbegrenzung angeordnet sindund dass am Eintritt des mindestens einen Nachbrennraumes (62, B, C, D, E) Einspritzmittel für Zusatzbrennstoff angeordnet sind.
- Brennkammer nach Anspruch 2, dadurch gekennzeichnet, dass der Vormischbrenner ein Doppelkegelbrenner (110) ohne mechanischen Flammenhalter ist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE4441235 | 1994-11-19 | ||
DE4441235A DE4441235A1 (de) | 1994-11-19 | 1994-11-19 | Brennkammer mit Mehrstufenverbrennung |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0713058A1 EP0713058A1 (de) | 1996-05-22 |
EP0713058B1 true EP0713058B1 (de) | 1998-05-13 |
Family
ID=6533665
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95810698A Expired - Lifetime EP0713058B1 (de) | 1994-11-19 | 1995-11-08 | Brennkammer mit Mehrstufenverbrennung |
Country Status (5)
Country | Link |
---|---|
US (1) | US5645410A (de) |
EP (1) | EP0713058B1 (de) |
JP (1) | JPH08219445A (de) |
CN (1) | CN1130741A (de) |
DE (2) | DE4441235A1 (de) |
Families Citing this family (37)
Publication number | Priority date | Publication date | Assignee | Title |
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ATE198788T1 (de) * | 1997-03-18 | 2001-02-15 | Alstom Power Schweiz Ag | Verfahren zum betrieb eines drallstabilisierten brenners sowie brenner zur durchführung des verfahrens |
US5997596A (en) * | 1997-09-05 | 1999-12-07 | Spectrum Design & Consulting International, Inc. | Oxygen-fuel boost reformer process and apparatus |
EP0918190A1 (de) * | 1997-11-21 | 1999-05-26 | Abb Research Ltd. | Brenner für den Betrieb eines Wärmeerzeugers |
DE19757189B4 (de) * | 1997-12-22 | 2008-05-08 | Alstom | Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers |
US6298654B1 (en) | 1999-09-07 | 2001-10-09 | VERMES GéZA | Ambient pressure gas turbine system |
DE10049205A1 (de) * | 2000-10-05 | 2002-05-23 | Alstom Switzerland Ltd | Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners |
DE10055408A1 (de) * | 2000-11-09 | 2002-05-23 | Alstom Switzerland Ltd | Verfahren zur Brenstoffeinspritzung in einen Brenner |
FR2825448B1 (fr) * | 2001-05-30 | 2003-09-12 | Inst Francais Du Petrole | Generateur thermique permettant de limiter les emissions d'oxydes d'azote par recombustion des fumees et procede pour la mise en oeuvre d'un tel generateur |
EP1262714A1 (de) * | 2001-06-01 | 2002-12-04 | ALSTOM (Switzerland) Ltd | Brenner mit Abgasrückführung |
DE10164099A1 (de) * | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Brenner mit gestufter Brennstoffeinspritzung |
US6929469B2 (en) * | 2002-02-28 | 2005-08-16 | North American Manufacturing Company | Burner apparatus |
FR2872887B1 (fr) * | 2004-07-07 | 2006-09-08 | Inst Francais Du Petrole | Procede de combustion homogene et generateur thermique utilisant un tel procede |
EP1828684A1 (de) * | 2004-12-23 | 2007-09-05 | Alstom Technology Ltd | Vormischbrenner mit mischstrecke |
US7402038B2 (en) * | 2005-04-22 | 2008-07-22 | The North American Manufacturing Company, Ltd. | Combustion method and apparatus |
US7832365B2 (en) * | 2005-09-07 | 2010-11-16 | Fives North American Combustion, Inc. | Submerged combustion vaporizer with low NOx |
JP2007113888A (ja) * | 2005-10-24 | 2007-05-10 | Kawasaki Heavy Ind Ltd | ガスタービンエンジンの燃焼器構造 |
EP2058590B1 (de) * | 2007-11-09 | 2016-03-23 | Alstom Technology Ltd | Verfahren zum Betrieb eines Brenners |
EP2220433B1 (de) * | 2007-11-27 | 2013-09-04 | Alstom Technology Ltd | Verfahren und vorrichtung zur verbrennung von wasserstoff in einem vormischbrenner |
US20100095649A1 (en) * | 2008-10-20 | 2010-04-22 | General Electric Company | Staged combustion systems and methods |
US20100223930A1 (en) * | 2009-03-06 | 2010-09-09 | General Electric Company | Injection device for a turbomachine |
US8202470B2 (en) * | 2009-03-24 | 2012-06-19 | Fives North American Combustion, Inc. | Low NOx fuel injection for an indurating furnace |
US20110219776A1 (en) * | 2010-03-15 | 2011-09-15 | General Electric Company | Aerodynamic flame stabilizer |
EP2644997A1 (de) | 2012-03-26 | 2013-10-02 | Alstom Technology Ltd | Mischanordnung zum Mischen von Kraftstoff mit einem Strom aus sauerstoffhaltigem Gas |
EP2888531B1 (de) * | 2012-08-24 | 2020-06-17 | Ansaldo Energia Switzerland AG | Sequenzielle verbrennung mit verdünnungsgasmischer |
AU2013219140B2 (en) | 2012-08-24 | 2015-10-08 | Ansaldo Energia Switzerland AG | Method for mixing a dilution air in a sequential combustion system of a gas turbine |
JP6231114B2 (ja) * | 2012-10-24 | 2017-11-15 | ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングGeneral Electric Technology GmbH | 希釈ガス混合器を備えた2段燃焼 |
US9194583B2 (en) * | 2013-02-20 | 2015-11-24 | Jorge DE LA SOVERA | Mixed fuel vacuum burner-reactor |
CN103277804B (zh) * | 2013-05-17 | 2015-07-22 | 江苏奥能耐火材料有限公司 | 一种烟气焚烧炉 |
EP2933559A1 (de) * | 2014-04-16 | 2015-10-21 | Alstom Technology Ltd | Kraftstoffmischanordnung und Brennkammer mit einer solchen Mischanordnung |
EP2957835B1 (de) | 2014-06-18 | 2018-03-21 | Ansaldo Energia Switzerland AG | Verfahren zur Rückführung von Abgas aus einer Brennkammer eines Brenners einer Gasturbine sowie Gasturbine zur Durchführung des Verfahrens |
CN104832912A (zh) * | 2015-04-08 | 2015-08-12 | 石家庄新华能源环保科技股份有限公司 | 一种多级接力燃烧装置 |
US10465907B2 (en) * | 2015-09-09 | 2019-11-05 | General Electric Company | System and method having annular flow path architecture |
CN106500102B (zh) * | 2016-11-04 | 2018-11-13 | 中国科学技术大学 | 一种可控热氛围燃烧器 |
CN106402856B (zh) * | 2016-11-22 | 2018-10-19 | 北京航空航天大学 | 一种连续、快速、大范围线性调节温度的高温燃气发生装置和方法 |
FI128444B (en) * | 2017-12-22 | 2020-05-15 | Valmet Technologies Oy | Method and apparatus for burning primary fuel |
CN113124422B (zh) * | 2020-01-13 | 2024-05-28 | 中国科学院工程热物理研究所 | 轴向分级燃烧器 |
CN114353121B (zh) * | 2022-01-18 | 2022-12-20 | 上海交通大学 | 一种用于燃气轮机的多喷嘴燃料注入方法 |
Family Cites Families (15)
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GB2098720B (en) * | 1979-01-12 | 1983-04-27 | Gen Electric | Stationary gas turbine combustor arrangements |
DE2937631A1 (de) * | 1979-09-18 | 1981-04-02 | Daimler-Benz Ag, 7000 Stuttgart | Brennkammer fuer gasturbinen |
GB2097113B (en) | 1981-04-22 | 1985-09-18 | Gen Electric | Low nox combustor |
DE3662462D1 (en) * | 1985-07-30 | 1989-04-20 | Bbc Brown Boveri & Cie | Dual combustor |
US4735052A (en) * | 1985-09-30 | 1988-04-05 | Kabushiki Kaisha Toshiba | Gas turbine apparatus |
JP2644745B2 (ja) * | 1987-03-06 | 1997-08-25 | 株式会社日立製作所 | ガスタービン用燃焼器 |
DE3707773C2 (de) | 1987-03-11 | 1996-09-05 | Bbc Brown Boveri & Cie | Einrichtung zur Prozesswärmeerzeugung |
CH674561A5 (de) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
US4928481A (en) * | 1988-07-13 | 1990-05-29 | Prutech Ii | Staged low NOx premix gas turbine combustor |
US5013236A (en) * | 1989-05-22 | 1991-05-07 | Institute Of Gas Technology | Ultra-low pollutant emission combustion process and apparatus |
US5158445A (en) * | 1989-05-22 | 1992-10-27 | Institute Of Gas Technology | Ultra-low pollutant emission combustion method and apparatus |
CH680467A5 (de) * | 1989-12-22 | 1992-08-31 | Asea Brown Boveri | |
CH682952A5 (de) * | 1991-03-12 | 1993-12-15 | Asea Brown Boveri | Brenner für eine Vormischverbrennung eines flüssigen und/oder gasförmigen Brennstoffes. |
EP0540167A1 (de) * | 1991-09-27 | 1993-05-05 | General Electric Company | Gestufte Vormischbrennkammer mit niedrigem NOx-Ausstoss |
GB2278431A (en) * | 1993-05-24 | 1994-11-30 | Rolls Royce Plc | A gas turbine engine combustion chamber |
-
1994
- 1994-11-19 DE DE4441235A patent/DE4441235A1/de not_active Withdrawn
-
1995
- 1995-11-08 DE DE59502165T patent/DE59502165D1/de not_active Expired - Fee Related
- 1995-11-08 EP EP95810698A patent/EP0713058B1/de not_active Expired - Lifetime
- 1995-11-15 JP JP7297079A patent/JPH08219445A/ja active Pending
- 1995-11-16 US US08/558,535 patent/US5645410A/en not_active Expired - Fee Related
- 1995-11-19 CN CN95118855A patent/CN1130741A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
DE59502165D1 (de) | 1998-06-18 |
CN1130741A (zh) | 1996-09-11 |
EP0713058A1 (de) | 1996-05-22 |
JPH08219445A (ja) | 1996-08-30 |
DE4441235A1 (de) | 1996-05-23 |
US5645410A (en) | 1997-07-08 |
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