EP0488556B1 - Sekundäre Vormischbrennstoffdüse mit integrierter Verwirbelungsvorrichtung - Google Patents
Sekundäre Vormischbrennstoffdüse mit integrierter Verwirbelungsvorrichtung Download PDFInfo
- Publication number
- EP0488556B1 EP0488556B1 EP19910310554 EP91310554A EP0488556B1 EP 0488556 B1 EP0488556 B1 EP 0488556B1 EP 19910310554 EP19910310554 EP 19910310554 EP 91310554 A EP91310554 A EP 91310554A EP 0488556 B1 EP0488556 B1 EP 0488556B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- diffusion
- delivery pipe
- premix
- nozzle
- 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
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Classifications
-
- 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
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
Definitions
- This invention relates to gas turbine combustors; and, in particular, to improvements in gas turbine combustors for the further diminishment of air pollutants such as nitrogen oxides (NOx).
- NOx nitrogen oxides
- the secondary or center nozzle provides the flame source for the operation of the combustor.
- the specific configuration of the present invention includes an annular array of primary nozzles each of which discharges into the primary combustion chamber and a central secondary nozzie which discharged into the second combustion chamber.
- These nozzles may all be described as diffusion nozzles in that each nozzle has an axial fuel delivery pipe and is surrounded at its discharge end by an air swirler which provides air for combustion to the fuel nozzle discharge.
- the inventors discovered that further reduction in the production of NOx can be achieved by altering the design of the central or secondary nozzle such that it may be described as a combined premix and diffusion nozzle.
- a relatively small amount of fuel is used to sustain a diffusion pilot whereas a premix section of the nozzle provides additional fuel for ignition of the main fuel supply from the upstream primary nozzles directed into the primary combustion chamber.
- a premix swirler is located at the boundary of the secondary flame zone and serves to stabilize and hold the flame in various operating modes.
- This premix swirler component is, however, exposed to high flame temperatures which can impact the life of the swirler.
- EP-A-0269824 discloses a premixed pilot nozzle for dry low NOx combustor.
- a dual mode, dual stage low NOx combustor includes a primary combustion chamber and a secondary combustion chamber separated by a throat region of reduced diameter. Fuel is input into the primary combustors by an annular array of diffusion type nozzles whereas in accordance with the invention fuel is input into the secondary combustor by a central combination premix and diffusion nozzle.
- US-A-3899881 discloses a combustion apparatus for gas turbine engines particularly adapted to reduce emissions to meet automotive requirements.
- the fuel is laid on the wall of a cylindrical prechamber and evaporated from the wall by combustion air which is introduced through a swirler at the upstream end of the prechamber.
- the inner surface of the prechamber is artificially roughened by a grid of grooves to improve fuel evaporation.
- the fuel is laid on the wall from an annular manifold extending around the upstream end of the prechamber through tangential orifices leading from the manifold into the interior of the prechamber.
- the fuel manifold is cooled and shielded from heat by an air jacket. More air enters through entrance ports distributed around the prechamber toward its downstream end.
- the resulting lean fuel-air mixture is delivered past an annular flow dam at the outlet of the prechamber into a combustion or reaction zone which is abruptly enlarged from the prechamber.
- the structure causes turbulent flow, recirculation, and good mixing
- the premix swirler is located upstream of the fuel injection point so that under no operating conditions will the swirler be in direct contact with the flame, thereby extending the life of the swirler.
- the invention as described in the above identified parent application is especially applicable to gas turbine combustors of the type which include two combustion chambers separated by a venturi throat region.
- An annular array of primary nozzles discharge fuel into an upstream or primary combustion chamber.
- the method of operation dictates that while under base load, the primary nozzles are flamed out whereas the single central or secondary nozzle supports combustion of premix fuel from the primary nozzles.
- the single central or secondary nozzle which has been characterized as a diffusion nozzle, is replaced by a diffusion piloted premix nozzle which reduces the fuel flow to the central diffusion flame from approximately 20 percent of the total fuel flow to about 2 percent of the total fuel flow for the entire combustor.
- the design thus simultaneously minimizes the percentage of total fuel flow in the combustor that burns as a diffusion flame (with high NOx emissions) but allows sufficient heat input to ignite the main premixed flow by using the pilot premixed flow (which has low NOx emissions).
- the premix swirler component previously located at the boundary of the secondary flame zone is now relocated to a point upstream of the fuel injection point.
- the premix swirler is made an integral part of the secondary fuel nozzle, and is located behind or upstream of the radial fuel distribution tubes.
- the swirler will preferably comprise a series of vanes circumferentially located at some angle with respect to the axial centerline of the fuel nozzle.
- a venturi is provided at the discharge end of the secondary premix chamber in order to assist in secondary flame stabilization.
- a gas turbine 12 includes a compressor 14, a combustor 16 and a turbine 18 represented by a single blade. Although it is not specifically shown, it is well known that the turbine is drivingly connected to the compressor along a common axis.
- the compressor 14 pressurizes inlet air which is then turned in direction or reverse flowed to the combustor 16 where it is used to cool the combustor and also used to provide air to the combustion process.
- the gas turbine includes a plurality of the combustors 16 (one shown) which are located about the periphery of the gas turbine. In one particular gas turbine model there are fourteen such combustors.
- a transition duct 20 connects the outlet end 18 of its particular combustor with the inlet end of the turbine to deliver the hot products of the combustion process to the turbine.
- each combustor 16 comprises a primary or upstream combustion chamber 24 and a second or downstream combustion chamber 26 separated by a venturi throat region 28.
- the combustor 16 is surrounded by a combustor flow sleeve 30 which channels compressor discharge air flow to the combustor.
- the combustor is further surrounded by an outer casing 31 ( Figure 1) which is bolted to the turbine casing 32.
- Primary nozzles 36 provide fuel delivery to the upstream combustor 24 and are arranged in an annular array around a central secondary nozzle 38.
- each combustor may include six primary nozzles and one secondary nozzle.
- fuel is delivered to the nozzles through plumbing 42 in a manner well known in the art and fully described in the aforementioned patent. Ignition in the primary combustor is caused by spark plug 48 shown in Figure 1 and in adjacent combustors by means of crossfire tubes 50 also well known in the art.
- a diffusion nozzle 36 includes a fuel delivery nozzle 54 and an annular swirler 56.
- the nozzle 54 delivers only fuel which is then subsequently mixed with swirler air for combustion.
- the secondary nozzle is also a diffusion nozzle as will be explained further.
- the dual stage, dual mode combustor is designed to operate in a premix mode such that all of the primary nozzles 36 are simply mixing fuel and air to be ignited by the diffusion flame supported by the secondary or central diffusion nozzle 38.
- This premixing of the primary nozzle fuel and ignition by the secondary diffusion nozzle led to a lower NOx output in the combustor.
- the invention simultaneously minimizes the percentage of total fuel in the combustor that burns as a diffusion flame (with high NOx emissions) while allowing sufficient heat input to ignite the main premixed flow by using the premixed secondary or pilot flow.
- the nozzle also referred to as a secondary nozzle, includes a diffusion pilot 62 having a fuel delivery pipe 64.
- the fuel delivery pipe includes an axial pipe portion 66 and a plurality of radial, blind ended fuel distribution tubes 68 which extend radially outwardly from the axial pipe portion. In the preferred embodiment, there are six such fuel distribution tubes.
- the fuel distribution tubes each include a plurality of fuel discharge holes or orifices 70 which direct fuel downstream toward the discharge end of the combined nozzle.
- the fuel distribution holes are sized so as to obtain the desired percentage of fuel flow into the premix chamber to be hereinafter described.
- the diffusion pilot 62 further includes an air delivery pipe 74 coaxial with and surrounding the fuel delivery axial pipe portion 66.
- the air input into the air delivery pipe 74 is compressor discharge air which is reverse flowed around the combustor 16 into the volume 76 ( Figures 1 and 2) defined by the flow sleeve 30 and the combustion chamber liner 78.
- the diffusion pilot 62 includes at its discharge end a first or diffusion pilot swirler 82 for the purpose of directing air delivery pipe discharge air to the diffusion pilot flame.
- a premix chamber 84 is defined by a sleeve-like truncated cone 85 which surrounds the diffusion pilot 62 and includes a discharge end (see flow arrows) terminating adjacent the diffusion pilot discharge end. Compressor discharge air is also reverse flowed into the premix chamber 84 from volume 76 in a manner similar to the manner in which air is supplied to the air delivery pipe 74.
- the plurality of radial fuel distribution tubes 68 extend through the air delivery pipe 74 and into the premix chamber 84 such that the fuel and air are mixed and delivered to a second or premix chamber swirler annulus 86 between the diffusion pilot 62 and the premix chamber truncated cone 85.
- a third or central nozzle swirler 90 is located downstream from the discharge end of the secondary nozzle 100 between an extension or cup 92 on the discharge end of the pilot and the centerbody wall 95 of the primary combustion chamber. Compressor air is also reverse flowed to this swirler from the volume 76 surrounding the combustion liners. The purpose of this third swirler 90 is to provide stability for the diffusion and premix nozzle flame when combining with the primary premix flow from the primary combustor.
- the required design of the first, second and third swirlers 82, 86 and 90, respectively, would be known to practitioners in the combustion art, and therefore requires no further description.
- the truncated cone 85 which defines the premix chamber 84, is formed of any metal suitable to use within a gas turbine environment.
- the diffusion piloted premix nozzle includes a diffusion pilot 104 having a fuel delivery pipe 106.
- the fuel delivery pipe has an axial pipe portion 108 and a plurality of radial fuel distribution tubes 110 which extend radially outwardly from the axial pipe portion 108 and which are closed at their outermost ends.
- a preferred arrangement includes six such fuel distribution tubes.
- Each tube 108 also includes a plurality of fuel discharge holes or orifices 112 at different radial locations which direct fuel downstream toward the discharge end of the secondary nozzle.
- the distribution holes 112 are sized so as to obtain the desired percentage of fuel flow into the premix chamber as described below.
- the diffusion pilot 104 further includes an air delivery pipe 114 coaxial with and surrounding the fuel delivery pipe 106.
- the air input into the air delivery pipe 114 is compressor discharge air which is reverse flowed around the combustor as described above in connection with the embodiment illustrated in Figure 3.
- the diffusion pilot 104 includes at its discharge end a first swirler annulus 116 for directing discharge air from the air delivery pipe into the diffusion pilot flame.
- a premix chamber 118 is defined by a sleeve 120 which surrounds the diffusion pilot 104 and includes a discharge end 119 terminating adjacent the diffusion pilot discharge end, i.e., adjacent the first swirler 116. Compressor discharge air is also reverse flowed into the premix chamber 118 as described hereinabove.
- the plurality of radial fuel distribution tubes 110 extend through the air delivery pipe 114 and into the premix chamber. However, in this embodiment, the second swirler annulus 122 is located upstream of the radial fuel distribution tubes 110. By so locating the swirler 122, it is at no time subjected to direct flame contact thereby extending the life of the swirler, while retaining the function of the previously described swirler 86.
- the air flow is substantially similar to that described in the Figure 3 embodiment in that the same degree of swirling of air and fuel is achieved so as to preserve the flame stability, but the danger of heat damage to the second swirler 122 is minimized.
- the flame characteristics are identical to the flame characteristics in the previously described embodiment, the result should be an identical or similar performance in premixed combustion as a whole.
- the second swirler 122 will be an integral part of the secondary fuel nozzle 102, and the swirler will consist of a series of vanes circumferentially located at some angle with respect to the axial center line of the fuel nozzle as will be understood by those of ordinary skill in the art.
- the vanes may be cast as part of the nozzle or made separately and mechanically attached via welding or brazing to the nozzle.
- the vanes may be aerodynamic or non-aerodynamic so as to result in an aerodynamic flow or a separated flow from the vanes. While it is presently preferred to utilize a non-aerodynamic scheme, aerodynamic vanes may be utilized as well.
- a diffusion piloted premix nozzle is disclosed which is identical to that illustrated in Figure 4 but with the addition of a venturi component 124 located at the end of the secondary premixing chamber.
- the venturi is not an integral part of the secondary fuel nozzle.
- the venturi 124 will supplement the swirl imparted by the upstream swirler 122 with a recirculating flow which will tend to enhance stabilization of the intense swirling flow.
- the foregoing invention as described produces less NOx while providing an opportunity to add to the fuel flow through the secondary nozzle because of the lower NOx output whereas the turn down ratio or the ability to operate under varying conditions is considerably widened because the diffusion pilot is subject to the premix flow of the pilot rather than the total overall premix flow from the surrounding primary nozzles.
- the service life of the premix swirler previously located at the discharge end of the premix chamber has been enhanced by relocation upstream of the fuel injection orifices of the diffusion pilot.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Claims (10)
- Diffusion-gesteuerte Vormischdüse (102) für eine Gasturbinen-Brennkammer, enthaltend eine Hülse (120); eine Diffusions-Steuerung (104) in der Hülse (120) und enthaltend eine Brennstoffversorgungsleitung (106) mit einem Einlaßende und einem Auslaßende und eine Luftversorgungsleitung (114); wobei die Brennstoffversorgungsleitung (106) ferner mehrere Brennstoffverteilungsrohre (110) aufweist, die sich radial weg von dem axialen Abschnitt (108) erstrecken; eine Vormischkammer (118), die die Diffusion-Steuerung (104) umgibt und ein Einlaßende und ein Auslaßende (119) aufweist, wobei die Brennstoffverteilungrohre (110) wenigstens eine Abgabeöffnung aufweisen, um Brennstoff in die Vormischkammer (118) abzugeben, gekennzeichnet durch:
einen Vormisch-Luftverwirbler (122), der in der Vormischkammer (118) stromaufwärts von den Brennstoffverteilungsrohren (110) angebracht ist und die Brennstoffversorgungsleitung (106) und die Luftversorgungsleitung (114) umgibt, wobei der Luftverwirbler (122) in der Lage ist, Luft in der Hülse außerhalb der Diffusion-Steuerung (104) zu empfangen und zu verwirbeln. - Diffusion-gesteuerte Vormischdüse (102) nach Anspruch 1, gekennzeichnet durch eine Venturi-Anordnung (124), die benachbart zu dem Auslaßende von der Diffusion-Steuerung (104) angeordnet ist.
- Diffusion-gesteuerte Vormischdüse (102) nach Anspruch 1, wobei die Brennstoffversorgungsleitung (106) einen axialen Abschnitt (108) mit einem Einlaßende aufweist und der Vormisch-Verwirbler (122) neben den Brennstoffverteilungsrohren (110) angebracht ist.
- Diffusion-gesteuerte Vormischdüse (102) nach Anspruch 3, wobei sich die Luftversorgungsleitung (114) im wesentlichen koaxial zu wenigstens einem Teil der Brennstoffversorgungsleitung (106) erstreckt und diese umgibt.
- Diffusion-gesteuerte Vormischdüse (102) nach Anspruch 3, wobei die radialen Brennstoffverteilungsrohre (110) in Richtung auf das Einlaßende der Vormischkammer (118) angeordnet sind.
- Diffusion-gesteuerte Vormischdüse (102) nach Anspruch 3, wobei die Brennstoffverteilungsrohre (110) jeweils mehrere Brennstoffabgabeöffnungen (112) aufweisen, die an unterschiedlichen radialen Stellen angeordnet sind zum Abgeben von Brennstoff in Richtung auf das Ausgangsende der Diffusion-Steuerung (104).
- Diffusion-gesteuerte Vormischdüse nach einem der Ansprüche 1 bis 6, wobei die Luftverteilungsleitung (114) die axiale Brennstoffversorgungsleitung (106) entlang im wesentlichen der gesamten Länge der axialen Brennstoffversorgungsleitung (106) umgibt.
- Diffusion-gesteuerte Vormischdüse nach einem der Ansprüche 1 bis 7, wobei ein Verwirbler-Ringraum (116) zwischen der Brennstoffversorgungsleitung (106) und der Luftversorgungsleitung (114) angeordnet ist.
- Gasturbinen-Brennkammer des Typs enthaltend erste und zweite Brennkammern (24,26), die durch einen Hals- bzw. Engstellenbereich (28) miteinander verbunden sind, der im Vergleich zu den ersten und zweiten Brennkammern (24,26) eine verkleinerte Abmessung hat; mehrere primäre Diffussions-Brennstoffdüsen (54) in einer Ringanordnung stromaufwärts von der ersten Brennkammer (24) zum Einführen von Brennstoff in die erste Brennkammer (24), wobei die Diffusionsdüsen jeweils einen Verwirbler-Ringraum (56) aufweisen zum Einführen von Druckluft in die erste Brennkammer (24), zum Erzeugen eines brennbaren Brennstoff-Luft-Gemisches; und eine Diffusion-gesteuerte Vormischdüse, wie sie in einem der Ansprüche 1 bis 6 beansprucht ist und die stromaufwärts von der zweiten Brennkammer (26) angeordnet ist und ein Auslaßende hat, das in die zweite Brennkammer (26) gerichtet ist.
- Gasturbinen-Brennkammer nach Anspruch 9, wobei die Difffusion-gesteuerte Vormischdüse (102) in der Mitte der Ringanordnung von primären Brennstoffdüsen (54) angeordnet ist und eine Venturi-Anordnung (124) zwischen der Diffusion-gesteuerten Vormischdüse (102) und der umgebenden Hülse (120) aufweist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US61824690A | 1990-11-27 | 1990-11-27 | |
US618246 | 2000-07-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0488556A1 EP0488556A1 (de) | 1992-06-03 |
EP0488556B1 true EP0488556B1 (de) | 1997-07-16 |
Family
ID=24476921
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19910310554 Expired - Lifetime EP0488556B1 (de) | 1990-11-27 | 1991-11-15 | Sekundäre Vormischbrennstoffdüse mit integrierter Verwirbelungsvorrichtung |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0488556B1 (de) |
JP (1) | JP2651304B2 (de) |
DE (1) | DE69126846T2 (de) |
NO (1) | NO300240B1 (de) |
RU (1) | RU2076276C1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7284378B2 (en) | 2004-06-04 | 2007-10-23 | General Electric Company | Methods and apparatus for low emission gas turbine energy generation |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5259184A (en) * | 1992-03-30 | 1993-11-09 | General Electric Company | Dry low NOx single stage dual mode combustor construction for a gas turbine |
US5218824A (en) * | 1992-06-25 | 1993-06-15 | Solar Turbines Incorporated | Low emission combustion nozzle for use with a gas turbine engine |
FR2706588B1 (fr) * | 1993-06-16 | 1995-07-21 | Snecma | Système d'injection de carburant pour chambre de combustion. |
GB9607010D0 (en) * | 1996-04-03 | 1996-06-05 | Rolls Royce Plc | Gas turbine engine combustion equipment |
WO1998025084A1 (en) * | 1996-12-04 | 1998-06-11 | Siemens Westinghouse Power Corporation | DIFFUSION AND PREMIX PILOT BURNER FOR LOW NOx COMBUSTOR |
EP1710505A2 (de) | 1999-12-15 | 2006-10-11 | Osaka Gas Co., Ltd. | Brenner, Gasturbinenantrieb und Kraft-Wärme-Kopplungsanlage |
JP2002031343A (ja) | 2000-07-13 | 2002-01-31 | Mitsubishi Heavy Ind Ltd | 燃料噴出部材、バーナ、燃焼器の予混合ノズル、燃焼器、ガスタービン及びジェットエンジン |
US6381964B1 (en) * | 2000-09-29 | 2002-05-07 | General Electric Company | Multiple annular combustion chamber swirler having atomizing pilot |
US6848260B2 (en) * | 2002-09-23 | 2005-02-01 | Siemens Westinghouse Power Corporation | Premixed pilot burner for a combustion turbine engine |
US7757491B2 (en) * | 2008-05-09 | 2010-07-20 | General Electric Company | Fuel nozzle for a gas turbine engine and method for fabricating the same |
DE102008026459A1 (de) * | 2008-06-03 | 2009-12-10 | E.On Ruhrgas Ag | Brenner, insbesondere für eine Verbrennungseinrichtung in einer Gasturbinenanlage |
US8240150B2 (en) * | 2008-08-08 | 2012-08-14 | General Electric Company | Lean direct injection diffusion tip and related method |
US20100192582A1 (en) * | 2009-02-04 | 2010-08-05 | Robert Bland | Combustor nozzle |
US20110107767A1 (en) * | 2009-11-06 | 2011-05-12 | General Electric Company | Secondary fuel nozzle venturi |
US9016039B2 (en) * | 2012-04-05 | 2015-04-28 | General Electric Company | Combustor and method for supplying fuel to a combustor |
US20140318140A1 (en) * | 2013-04-25 | 2014-10-30 | Jeremy Metternich | Premixer assembly and mechanism for altering natural frequency of a gas turbine combustor |
JP6945468B2 (ja) * | 2018-02-06 | 2021-10-06 | 三菱パワー株式会社 | ガスタービン燃焼器、ガスタービン及びガスタービン燃焼器の制御方法 |
RU2765667C2 (ru) * | 2019-12-30 | 2022-02-01 | Публичное акционерное общество "ОДК-Кузнецов" (ПАО "ОДК-Кузнецов") | Устройство перепуска воздуха и газотурбинный двигатель, содержащий устройство перепуска воздуха |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3899881A (en) * | 1974-02-04 | 1975-08-19 | Gen Motors Corp | Combustion apparatus with secondary air to vaporization chamber and concurrent variance of secondary air and dilution air in a reverse sense |
DE3241162A1 (de) * | 1982-11-08 | 1984-05-10 | Kraftwerk Union AG, 4330 Mülheim | Vormischbrenner mit integriertem diffusionsbrenner |
EP0269824B1 (de) * | 1986-11-25 | 1990-12-19 | General Electric Company | Kombinierter Diffusions- und Vormischpilotbrenner |
JPH076630B2 (ja) * | 1988-01-08 | 1995-01-30 | 株式会社日立製作所 | ガスタービン燃焼器 |
JP2865684B2 (ja) * | 1989-01-06 | 1999-03-08 | 株式会社日立製作所 | ガスタービン燃焼器 |
-
1991
- 1991-11-15 DE DE1991626846 patent/DE69126846T2/de not_active Expired - Lifetime
- 1991-11-15 EP EP19910310554 patent/EP0488556B1/de not_active Expired - Lifetime
- 1991-11-25 JP JP3334501A patent/JP2651304B2/ja not_active Expired - Lifetime
- 1991-11-26 NO NO914632A patent/NO300240B1/no not_active IP Right Cessation
- 1991-11-26 RU SU5010115 patent/RU2076276C1/ru active
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7284378B2 (en) | 2004-06-04 | 2007-10-23 | General Electric Company | Methods and apparatus for low emission gas turbine energy generation |
Also Published As
Publication number | Publication date |
---|---|
NO300240B1 (no) | 1997-04-28 |
RU2076276C1 (ru) | 1997-03-27 |
JP2651304B2 (ja) | 1997-09-10 |
DE69126846T2 (de) | 1998-02-12 |
NO914632D0 (no) | 1991-11-26 |
JPH04283316A (ja) | 1992-10-08 |
NO914632L (no) | 1992-05-29 |
EP0488556A1 (de) | 1992-06-03 |
DE69126846D1 (de) | 1997-08-21 |
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