US3735930A - Fuel injection nozzle - Google Patents
Fuel injection nozzle Download PDFInfo
- Publication number
- US3735930A US3735930A US00184676A US3735930DA US3735930A US 3735930 A US3735930 A US 3735930A US 00184676 A US00184676 A US 00184676A US 3735930D A US3735930D A US 3735930DA US 3735930 A US3735930 A US 3735930A
- Authority
- US
- United States
- Prior art keywords
- nozzle
- apertures
- cover
- combustion chamber
- tip
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2220/00—Application
- F05B2220/30—Application in turbines
- F05B2220/302—Application in turbines in gas turbines
Definitions
- ABSTRACT A fuel nozzle structure for a combustion chamber, the downstream portion of the nozzle structure having a plurality of hollow nozzle inserts I disposed therethrough, and a nozzle cover in spaced relation with the downstream nozzle portion and defining a cooling air passageway therebetween.
- the nozzle inserts project into apertures in the nozzle cover so that fuel can be projected through the cover and into the combustion chamber and the inserts being in spaced relation with the cover so as to allow cooling airflowing through the passageway to flow into the combustion chamber.
- This fuel nozzle structure prevents residues from collecting on the downstream nozzle portion.
- the present invention relates to combustion chambers for gas turbines, and more specifically to the fuel nozzle structures disposed therein.
- One of the problems with conventional fuel nozzle structures used in combustion chambers is that the downstream portion of the nozzle is exposed to the very high temperature region within the combustion chamber and the downstream portion therefore becomes exceedingly hot.
- the high temperature of the downstream nozzle portion causes the volatile components in the fuels to leave viscous solid residues to adhere on the inner or upstream surface of the downstream nozzle portion. Once some of these solids accumulate on the nozzle downstream portion, the residue further accumulates on the initial deposited residue. Residues continue to adhere and accumulate to eventually begin to block the nozzle apertures.
- the downstream nozzle portion as a consequence of the accumulation of residues on the upstream side of the downstream nozzle portion, becomes more heated since the residues prevent the nozzle from being properly cooled. Furthermore, the accumulation -of the residues at the fuel injection apertures creates uneven fuel flow and produces a greater pressure loss, even though the apertures are designed so that the pressure losses will be at a minimum.
- the pressure to supply the fuel must be raised to make up for the loss equivalent to the decrease in the area of the apertures. The increase in pressure produces an increase in the power consumption of the compressor, and an overall decrease in turbine efficiency results.
- the residue contains considerable amounts of corrosive substances, such as sulfur, and the high temperature of the nozzle promotes the corrosion of the base material of the nozzle resulting in a shutdown of the turbine.
- the nozzle must be regularly detached for the purposes of cleaning and replacement, and it is extremely difficult to replace the nozzle during operation because thecombustion chamber within the turbine is normally surrounded with pressurized air. It is a severe disadvantage to the gas turbine power plant to stop the turbine to replace the nozzle.
- a combustion chamber having a nozzle structure dis posed therein at the downstream end thereof.
- a nozzle structure dis posed therein at the downstream end thereof.
- a plurality of fuel exit apertures in which is disposed a corresponding plurality of nozzle inserts to inject fuel from the nozzle structure into the combustion chamber.
- a nozzle cover structure in spaced relation with the nozzle and defining a cooling fluid passageway therebetween.
- the nozzle inserts project into corresponding apertures in the nozzle cover and are in spaced relation with the nozzle structure to allow cooling fluid to pass through the passageway and out through the apertures in the nozzle cover.
- the nozzle cover prevents the nozzle from being exposed to the very high temperature of the combustion chamber, and, by defining a passageway therebetween, allows for cooling fluid to cool the nozzle structure. This minimizes the amount of solid residues which are deposited on the nozzle structure and further prevents the clogging of the fuel passages. Far less maintenance is required on the nozzle structure and corrosion of the nozzle structure is minimized.
- the operating life of the nozzle structure is substantially increased enabling a substantial continuing generating of power from the turbine power plant.
- FIG. 1 shows a longitudinal sectional view of a portion of a gas turbine power plant having a conventional nozzle structure
- FIG. 2 shows a longitudinal sectional view of a portion of a gas turbine power plant having a nozzle structure build in accordance with the present invention
- FIG. 3 shows an enlarged portion of the nozzle structure shown in FIG. 2;
- FIG. 4 is a view taken along line IV--IV in FIG. 3;
- FIG. 5 is a' longitudinal view of another embodiment of the present invention.
- FIG. 1 there is shown a portion of a gas turbine combustion section 10 comprising an annular outer casing structure 11 and a portion of the combustion chamber 13, disposed concentrically therein.
- the combustion chamber 13 has a fuel nozzle structure 15 which is detachably secured to the upstream portion of the combustion chamber 13.
- the combustion chamber 13 is secured to an annular combustor holder 16 which, in turn, is secured to the vertical wall portion of the outer casing 11.
- An annular baffle swirler structure 18 is secured to the vertical wall of the outer casing 1 l and is disposed between the combustor holder 16 and the fuel nozzle 15, in spaced relation therebetween.
- a plurality of apertures 20 are radially disposed in the combustion holder 16 to provide fluid communication between a plenum chamber 22 and a passageway 23, which leads to the combustion chamber 13.
- a plurality of apertures 25 are disposed around the baffle swirler 18 which allows cooling air from passage way 23 to flow therethrough into the combustion chamber.
- the conventional fuel nozzle structure 15 is comprised of a downstream nozzle tip portion 27, having fuel apertures 28 disposed therearound to admit fuel into the combustion chamber 13.
- the fuel nozzle 15 has the downstream surface of the nozzle tip 27 exposed to the high temperature region in the combustion chamber and thereby becomes exceedingly hot, primarily due to the radiation generated from the flame. Consequently, fuel residues collect on the upstream surface of the nozzle tip 27 and continue to build up' until the fuel injection apertures 28 become partially blocked. This results in a pressure loss, and inefficient gas turbine operation, and the residue, in fact, prevents proper cooling of the nozzle tip portion 27. Finally, corrosion is promoted on the base material of the nozzle tip 27 and reg ular cleaning and replacement are necessary, resulting in stoppage of the gas turbine power plant.
- FIG. 2 there is shown a partial view of a combustion chamber 34 similar to that shown in FIG, 1, where represents the outer casing of the combustion portion of the gas turbine power plant.
- An annular holder structure 31 is secured to the casing 30 by any suitable means such as bolts 32.
- the upstream domeshaped portion of the combustion chamber 34 is secured to the radially inner surface of the holder 31.
- a baffle swirler structure 36 is also secured to the outer casing structure 30 and is in spaced relation with the holder 31.
- the baffle 36 is in spaced relation with the dome portion of the combustion chamber 34 jointly defining annular passageway 37.
- a fuel injection nozzle structure 39 is secured to the outer casing 30, by any suitable means such as bolts 41.
- the nozzle projects into the dome portion of the combustion chamber 34.
- the downstream tip portion 42 of the nozzle 30 is protected by a nozzle cover structure 43, which is disposed in a spaced relation with the nozzle tip 42 and, cooperatively therewith, defines passageway 45.
- the nozzle cover 43 is secured to the baffle swirler structure 36, by any suitable means such as bolts 46.
- a plurality of circumferentially spaced radial apertures 48 are disposed around the holder 31 to provide fluid communication between a pressurized plenum chamber 50 and the passageway 37.
- the chamber 50 is partially defined by the outer casing 30 and the combustion chamber.
- disposed around the baffle swirler structure 36 is a corresponding plurality of air inlet apertures 50.
- a plurality of smaller air inlet apertures 52 disposed circumferentially around the nozzle cover 43 to permit fluid communication with the cooling air passageway 45.
- nozzle insert structures 53 dis.- posed in corresponding apertures in the nozzle tip.
- the nozzle inserts 53 are screw threaded into the body of the nozzle tip 42 and project through the air cooling passageway 45 and into a corresponding aperture 54 in the nozzle cover 43.
- the insert 53 is in spaced relation with the nozzle cover 43 and defines an annular gap 56.
- the inner wall portion 58 of the insert 53 is flared at the downstream portion of the insert to thereby increase the cross-sectional area at the downstream portion of the insert.
- a cooling fin 60 (FIGS. 3 and 4) is disposed around the downstream portion of the insert 53.
- cooling air passes from the plenum chamber 50 (FIG. 2) through apertures 48 into passageway 37, a portion of the air also passing through apertures 50.
- the cooling air through apertures 50 passes through apertures 52 into passageway 45.
- the cooling air passes through the apertures 48, 50 and 52 because of the pressure differential between the plenum chamber 50 and the combustion chamber 34.
- the air flowing into passageway 45 continues therethrough and passes through gap 56 (FIG. 3) and then out the aperture 54 in the nozzle cover 43.
- Fuel meanwhile, is passing through the fuel injection nozzle structure 39 and is injected through the nozzle insert 53 into the combustion chamber 34.
- the cooling air around the nozzle insert 53 at gap 56 easily flows out into the combustion chamber, because it is absorbed in the fuel flow by an ejector effect.
- the cooling fin 60 protects the outer casing 62, and the combustor 64.
- An annular baf- I fle swirler structure 66 is securedly fastened within the combustor 64 and a nozzle cover 68 is provided between the baffle structure 66 and the nozzle 65.
- Disposed at the downstream tip of the nozzle are the nozzle inserts 70, which are disposed in a similar manner to that described in connection with FIG. 2.
- This embodiment is designed so that pressurized air in the plenum chamber 63 passes through a cooling structure 72, as indicated by the dashed connection 71, and then into a cooling flow passageway 73 in the nozzle structure 65.
- the cooling flow passageway 73 is in fluid communication with air flow passageway 74 which provides the cooling air to the nozzle tip portion 69. This eliminates apertures in the nozzle cover such as those shown at 52 in FIG. 2 and provides for cooler air to thenozzle tip.
- the outer surface of the nozzle tip is not directly exposed to the high temperature flame within the combustion chamber.
- the nozzle tip therefore operates at a substantially lower temperature than conventional nozzles. This prevents the accumulation of solid residues on the inner surface of the nozzle tip.
- fuel residues such as tars are deposited on the hot nozzle surface and tend to carbonize, building up a hard solid deposit with the increased fuel pressure loss and corrosive effects previously discussed.
- the improved nozzle tip herein disclosed runs much cooler and no solid residues build up on it, so that the undesirable effects of such deposits do not occur.
- the disclosed nozzle can be utilized in a combustion chamber for a much longer period of time without being cleaned or replaced and, correspondingly, the gas turbine power plant can operate for a far longer period of time than at present.
- a combustion chamber having a fuel nozzle structure to inject fuel therein
- said nozzle structure having a downstream nozzle tip portion
- a nozzle cover structure surrounding the downstream tip portion of the nozzle, said cover structure shielding the nozzle tip portion from the heat generated in said combustion chamber,
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Spray-Type Burners (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP1970118098U JPS4931059Y1 (ja) | 1970-11-30 | 1970-11-30 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3735930A true US3735930A (en) | 1973-05-29 |
Family
ID=33276033
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00184676A Expired - Lifetime US3735930A (en) | 1970-11-30 | 1971-09-29 | Fuel injection nozzle |
Country Status (3)
Country | Link |
---|---|
US (1) | US3735930A (ja) |
JP (1) | JPS4931059Y1 (ja) |
CA (1) | CA947099A (ja) |
Cited By (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3886736A (en) * | 1972-11-09 | 1975-06-03 | Westinghouse Electric Corp | Combustion apparatus for gas turbine |
US3917443A (en) * | 1974-10-07 | 1975-11-04 | Vernon Adams | Gaseous fuel burner |
FR2336556A1 (fr) * | 1975-12-24 | 1977-07-22 | Gen Electric | Injecteur de carburant perfectionne pour turbine a gaz |
US4373342A (en) * | 1977-02-04 | 1983-02-15 | Rolls-Royce Limited | Combustion equipment |
US4653278A (en) * | 1985-08-23 | 1987-03-31 | General Electric Company | Gas turbine engine carburetor |
US4934145A (en) * | 1988-10-12 | 1990-06-19 | United Technologies Corporation | Combustor bulkhead heat shield assembly |
EP0638768A2 (en) * | 1993-08-09 | 1995-02-15 | United Technologies Corporation | Fuel nozzle with non-axisymmetrical secondary spray |
US6082113A (en) * | 1998-05-22 | 2000-07-04 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
US6289676B1 (en) | 1998-06-26 | 2001-09-18 | Pratt & Whitney Canada Corp. | Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles |
US6378310B1 (en) * | 1998-01-28 | 2002-04-30 | Institut Francais Du Petrole | Combustion chamber of a gas turbine working on liquid fuel |
US6453673B1 (en) * | 2000-08-31 | 2002-09-24 | General Electric Company | Method of cooling gas only nozzle fuel tip |
EP1288575A3 (en) * | 2001-08-29 | 2004-04-21 | Hitachi, Ltd. | Gas turbine combustor and operating method |
US20050217270A1 (en) * | 2004-04-02 | 2005-10-06 | Pratt & Whitney Canada Corp. | Fuel injector head |
US20070006587A1 (en) * | 2004-03-03 | 2007-01-11 | Masataka Ohta | Combustor |
US20090230215A1 (en) * | 2008-03-11 | 2009-09-17 | Microjet Gmbh | Apparatus for generating and spraying an aerosol |
US20100089021A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Method and apparatus of introducing diluent flow into a combustor |
US20100089022A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Method and apparatus of fuel nozzle diluent introduction |
US20100092896A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Method and apparatus for introducing diluent flow into a combustor |
US20100089020A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Metering of diluent flow in combustor |
EP2211108A2 (en) * | 2009-01-22 | 2010-07-28 | General Electric Company | Nozzle for a turbomachine |
US20100281872A1 (en) * | 2009-05-06 | 2010-11-11 | Mark Allan Hadley | Airblown Syngas Fuel Nozzle With Diluent Openings |
US20100281871A1 (en) * | 2009-05-06 | 2010-11-11 | Mark Allan Hadley | Airblown Syngas Fuel Nozzle with Diluent Openings |
WO2010136287A2 (en) * | 2009-05-27 | 2010-12-02 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
US20130139513A1 (en) * | 2009-10-07 | 2013-06-06 | Pratt & Whitney Canada Corp. | Fuel nozzle and method of repair |
US20140041389A1 (en) * | 2011-03-30 | 2014-02-13 | Mitsubishi Heavy Industries, Ltd. | Nozzle, gas turbine combustor and gas turbine |
US20150285502A1 (en) * | 2014-04-08 | 2015-10-08 | General Electric Company | Fuel nozzle shroud and method of manufacturing the shroud |
EP1865260B1 (en) * | 2006-06-05 | 2020-04-08 | General Electric Company | Stage one turbine nozzle |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3153438A (en) * | 1961-04-17 | 1964-10-20 | Witold B Brzozowski | Dual fuel burner |
US3211207A (en) * | 1965-01-22 | 1965-10-12 | Sun Ray Burner Mfg Corp | Air diffuser for oil burner |
US3226038A (en) * | 1965-04-20 | 1965-12-28 | Vapor Corp | Combustor for a steam generator |
US3285240A (en) * | 1963-07-10 | 1966-11-15 | Indugas Ges Fur Ind Gasverwend | Industrial gas burner |
US3563470A (en) * | 1967-10-03 | 1971-02-16 | Director Of National Aerospace | Air swirling vanes for burner |
-
1970
- 1970-11-30 JP JP1970118098U patent/JPS4931059Y1/ja not_active Expired
-
1971
- 1971-09-29 US US00184676A patent/US3735930A/en not_active Expired - Lifetime
- 1971-10-19 CA CA125,457A patent/CA947099A/en not_active Expired
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3153438A (en) * | 1961-04-17 | 1964-10-20 | Witold B Brzozowski | Dual fuel burner |
US3285240A (en) * | 1963-07-10 | 1966-11-15 | Indugas Ges Fur Ind Gasverwend | Industrial gas burner |
US3211207A (en) * | 1965-01-22 | 1965-10-12 | Sun Ray Burner Mfg Corp | Air diffuser for oil burner |
US3226038A (en) * | 1965-04-20 | 1965-12-28 | Vapor Corp | Combustor for a steam generator |
US3563470A (en) * | 1967-10-03 | 1971-02-16 | Director Of National Aerospace | Air swirling vanes for burner |
Cited By (48)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3886736A (en) * | 1972-11-09 | 1975-06-03 | Westinghouse Electric Corp | Combustion apparatus for gas turbine |
US3917443A (en) * | 1974-10-07 | 1975-11-04 | Vernon Adams | Gaseous fuel burner |
FR2336556A1 (fr) * | 1975-12-24 | 1977-07-22 | Gen Electric | Injecteur de carburant perfectionne pour turbine a gaz |
US4070826A (en) * | 1975-12-24 | 1978-01-31 | General Electric Company | Low pressure fuel injection system |
US4373342A (en) * | 1977-02-04 | 1983-02-15 | Rolls-Royce Limited | Combustion equipment |
US4653278A (en) * | 1985-08-23 | 1987-03-31 | General Electric Company | Gas turbine engine carburetor |
US4934145A (en) * | 1988-10-12 | 1990-06-19 | United Technologies Corporation | Combustor bulkhead heat shield assembly |
EP0638768A2 (en) * | 1993-08-09 | 1995-02-15 | United Technologies Corporation | Fuel nozzle with non-axisymmetrical secondary spray |
EP0638768A3 (en) * | 1993-08-09 | 1995-08-16 | United Technologies Corp | Fuel nozzle with non-rotationally symmetrical, secondary atomization. |
US6378310B1 (en) * | 1998-01-28 | 2002-04-30 | Institut Francais Du Petrole | Combustion chamber of a gas turbine working on liquid fuel |
US6082113A (en) * | 1998-05-22 | 2000-07-04 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
US6289676B1 (en) | 1998-06-26 | 2001-09-18 | Pratt & Whitney Canada Corp. | Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles |
US6453673B1 (en) * | 2000-08-31 | 2002-09-24 | General Electric Company | Method of cooling gas only nozzle fuel tip |
US6460326B2 (en) * | 2000-08-31 | 2002-10-08 | William Theodore Bechtel | Gas only nozzle |
EP1288575A3 (en) * | 2001-08-29 | 2004-04-21 | Hitachi, Ltd. | Gas turbine combustor and operating method |
US20050000222A1 (en) * | 2001-08-29 | 2005-01-06 | Hitachi, Ltd. | Gas turbine combustor and operating method thereof |
US7117677B2 (en) | 2001-08-29 | 2006-10-10 | Hitachi, Ltd. | Gas turbine combustor and operating method thereof |
JP2010156350A (ja) * | 2001-08-29 | 2010-07-15 | Hitachi Ltd | ガスタービン燃焼器およびガスタービン燃焼器の運転方法 |
US20070006587A1 (en) * | 2004-03-03 | 2007-01-11 | Masataka Ohta | Combustor |
US7694521B2 (en) * | 2004-03-03 | 2010-04-13 | Mitsubishi Heavy Industries, Ltd. | Installation structure of pilot nozzle of combustor |
US20050217270A1 (en) * | 2004-04-02 | 2005-10-06 | Pratt & Whitney Canada Corp. | Fuel injector head |
US7117678B2 (en) * | 2004-04-02 | 2006-10-10 | Pratt & Whitney Canada Corp. | Fuel injector head |
EP1865260B1 (en) * | 2006-06-05 | 2020-04-08 | General Electric Company | Stage one turbine nozzle |
US20090230215A1 (en) * | 2008-03-11 | 2009-09-17 | Microjet Gmbh | Apparatus for generating and spraying an aerosol |
US20100092896A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Method and apparatus for introducing diluent flow into a combustor |
US20100089020A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Metering of diluent flow in combustor |
CN101725975A (zh) * | 2008-10-14 | 2010-06-09 | 通用电气公司 | 燃烧器中的稀释剂流的测量 |
US20100089022A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Method and apparatus of fuel nozzle diluent introduction |
US9121609B2 (en) | 2008-10-14 | 2015-09-01 | General Electric Company | Method and apparatus for introducing diluent flow into a combustor |
US20100089021A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Method and apparatus of introducing diluent flow into a combustor |
US8567199B2 (en) * | 2008-10-14 | 2013-10-29 | General Electric Company | Method and apparatus of introducing diluent flow into a combustor |
EP2211108A2 (en) * | 2009-01-22 | 2010-07-28 | General Electric Company | Nozzle for a turbomachine |
EP2211108A3 (en) * | 2009-01-22 | 2013-07-31 | General Electric Company | Nozzle for a turbomachine |
US20100281872A1 (en) * | 2009-05-06 | 2010-11-11 | Mark Allan Hadley | Airblown Syngas Fuel Nozzle With Diluent Openings |
US8607570B2 (en) * | 2009-05-06 | 2013-12-17 | General Electric Company | Airblown syngas fuel nozzle with diluent openings |
US20100281871A1 (en) * | 2009-05-06 | 2010-11-11 | Mark Allan Hadley | Airblown Syngas Fuel Nozzle with Diluent Openings |
CN102597632A (zh) * | 2009-05-27 | 2012-07-18 | 西门子公司 | 燃烧器、操作方法和组装方法 |
WO2010136287A3 (en) * | 2009-05-27 | 2012-05-18 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
US20100300104A1 (en) * | 2009-05-27 | 2010-12-02 | Boettcher Andreas | Burner, operating method and assembly method |
WO2010136287A2 (en) * | 2009-05-27 | 2010-12-02 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
CN102597632B (zh) * | 2009-05-27 | 2016-08-24 | 西门子公司 | 燃烧器、操作方法和组装方法 |
RU2541482C2 (ru) * | 2009-05-27 | 2015-02-20 | Сименс Акциенгезелльшафт | Горелка и газовая турбина, содержащая такую горелку |
US9127842B2 (en) * | 2009-05-27 | 2015-09-08 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
US20130139513A1 (en) * | 2009-10-07 | 2013-06-06 | Pratt & Whitney Canada Corp. | Fuel nozzle and method of repair |
US9599022B2 (en) * | 2009-10-07 | 2017-03-21 | Pratt & Whitney Canada Corp. | Fuel nozzle and method of repair |
US8826666B2 (en) * | 2011-03-30 | 2014-09-09 | Mitsubishi Heavy Industries, Ltd. | Nozzle, and gas turbine combustor having the nozzle |
US20140041389A1 (en) * | 2011-03-30 | 2014-02-13 | Mitsubishi Heavy Industries, Ltd. | Nozzle, gas turbine combustor and gas turbine |
US20150285502A1 (en) * | 2014-04-08 | 2015-10-08 | General Electric Company | Fuel nozzle shroud and method of manufacturing the shroud |
Also Published As
Publication number | Publication date |
---|---|
JPS4931059Y1 (ja) | 1974-08-22 |
CA947099A (en) | 1974-05-14 |
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