CN102906500A - Swirl blade, burner and gas turbine - Google Patents

Swirl blade, burner and gas turbine Download PDF

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Publication number
CN102906500A
CN102906500A CN2010800483863A CN201080048386A CN102906500A CN 102906500 A CN102906500 A CN 102906500A CN 2010800483863 A CN2010800483863 A CN 2010800483863A CN 201080048386 A CN201080048386 A CN 201080048386A CN 102906500 A CN102906500 A CN 102906500A
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CN
China
Prior art keywords
fuel
turbulence blades
distributor
nozzle
burner
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Granted
Application number
CN2010800483863A
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Chinese (zh)
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CN102906500B (en
Inventor
A.贝彻
M.卡诺沃尔夫
A.克鲁格
T.克里格
S.斯塔灵
U.沃兹
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Siemens AG
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Siemens AG
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Publication date
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Expired - Fee Related legal-status Critical Current
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    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • 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
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacture, Treatment Of Glass Fibers (AREA)

Abstract

The invention relates to a swirl blade (19) comprising a first gas nozzle set (21) and a further additional second gas nozzle set (23). Said nozzles (21) are fed by a first distributor pipe (61) and the nozzles (23) by a second distributor pipe (65), the distributor pipe (61, 65) being integrated into the swirl blade (19) which is embodied as two blade halves (19a, 19b) separated between the first distributor pipe (61) and the second distributor pipe (65). The invention also relates to a burner and a gas turbine.

Description

Turbulence blades, burner and gas turbine
Technical field
The present invention relates to the turbulence blades of burner in a kind of especially gas turbine.The invention still further relates in addition a kind of burner and a kind of gas turbine.
Background technology
Be devoted to reduce the emissions figure of burner in the gas turbine especially in view of the whole world, developed in recent years the low especially burner of some nitrogen oxide (NOx) discharge capacity.Very valuable in this respect is that these burners not only can be used a kind of fuel work, but also can for example press choice for use oil and gas or their combination with different fuel works as far as possible, to improve supply of material security and operation flexibility.These burners for example in EP0276696B1, have been introduced.
The burner of introducing in EP0276696B1 is a kind of as especially being used in the mixed burner in the gas-turbine plant, is used for fuel gas and/or oily premixed work.This burner comprises a center fuel feedway, wherein also is integrated with a control combustion device system, and it is as so-called diffusion flame burner or can be with fuel gas and/or oil work as premix burner independently.In addition also regulation might be supplied with inert substance.The center fuel feedway is centered on by the main burner system, this main burner system has an air fed circular passage system, comprises being in the turbulence blades of a plurality of blades group wherein to be arranged and be located at the blade upstream being used for jet pipe with fuel gas premixed work.In addition in fuel supply system, also have the entry nozzle of oil in turbulence blades group zone, they can be with main air flow and oily premixed.
Replace as in EP0276696B1 by the jet pipe that is in the blade upstream, also can fuel gas be sprayed in the air duct by the spout that is located in the turbulence blades itself, that for example introduces in EP0580683B1 is such.
In order to control discharging and can also further to improve combustion stability future, except for example in EP0580683B1, passing through like that also should to utilize another fuel gas nozzle by blade the fuel gas nozzle of blade.The separately acceptor's fuel gas level control of this additional fuel gas nozzle that is to say, except so far already present fuel gas and oily passage, must add the second fuel gas passage that adds in the center fuel feedway of burner.Present difficult point is to have the satisfied necessary strength specification of turbulence blades of additional fuel gas passage, and meanwhile arranged long service life.
Summary of the invention
Therefore the technical problem to be solved in the present invention provides a kind of favourable turbulence blades of the second fuel gas nozzle that has the first fuel gas nozzle and add in addition.The technical problem that the present invention second will solve is that a kind of favourable burner is provided.Another technical problem that will solve provides a kind of favourable gas turbine.
First technical problem is solved by turbulence blades claimed in claim 1 by a kind of, second technical problem is by being solved by burner claimed in claim 9, and another technical problem is by being solved by gas turbine claimed in claim 10.Dependent claims contains favourable expansion designs more of the present invention.
By this turbulence blades of the present invention, comprise the first fuel gas nozzle and the second fuel gas nozzle that adds in addition here,, wherein, the first nozzle is supplied with by the first distributor tube, and second nozzle is supplied with by the second distributor tube, here, distributor tube is integrated in the turbulence blades.Turbulence blades and give the distributor tube feed fuels or a kind of fuel supply system of fuel mixture has a fuel flow direction.
Known by the present invention, if the blade nozzle designs equally at lower region and upper zone, then cause two cooperate (Doppelpassung).Therefore also no longer can for example be undertaken by the adjustment pad that exists by a point of rotation the adjustment of blades oriented.Now based on a plurality of nozzle-axis and two the cooperation, so no longer there is the real point of rotation.
Therefore by the present invention, the turbulence blades between the first distributor tube and the second distributor tube is designed to be divided into two turbulence blades half ones.
Advantageously, present blade or two blade half ones, their orientation can be undertaken by adjusting pad again.In addition, can by two independently distributor tube implement respectively fuel control.The partition type blade can also be made simple and cheaply.
Preferably, described two turbulence blades half ones have a flow direction when work, and are connected with the first and second fuel distributor passages respectively in the upstream, and wherein, the first and second fuel distributor passages are located in the center fuel feedway.Here, these turbulence blades half ones are installed in the annular air channel of supplying with combustion air.
Therefore, from the fuel of the first fuel distributor passage, from the fuel of the second fuel distributor passage, can spray into independently of one another in the first distributor tube or the second distributor tube in.Can realize thus these fuel distributor passages and thereby different " classification (staging) " of fuel of turbulence blades half one.This is when conversion or be favourable when flushing between full load and sub-load just in time, because can avoid thermal stress by feed fuels fully independently, and can very rapidly realize on the other hand conversion.
Preferably, these turbulence blades half ones are installed in the annular air channel of supplying with combustion air, it is around the center fuel feedway, wherein, the first fuel nozzle is supplied with by the first fuel distributor feedway in the center fuel feedway, and the second fuel nozzle is supplied with by the second fuel distributor passage in the center fuel feedway.
In addition, by preferred design, the fuel distributor feedway has a flow direction and comprises a supply pipe, it is connected with one of turbulence blades in the downstream, and comprise an annular adapter (Ringaufsatz), wherein, supply pipe is connected with annular adapter in the upstream, wherein, annular adapter is seen along the flow direction and is connected to fuel distributor passage upstream.
Preferably, described two turbulence blades half ones have in the downstream and cooperate plug and have attached slide in the upstream.Wherein, slide in the upstream at least part of stretching in the center fuel feedway.Here, described two blades, half quality award from the ministry selection of land is only inserted and is cooperated in the plug.Therefore two blade half ones can thermal expansion.Thereby can avoid thermal stress.Also thereby prolong service life of whole burner service life that thus can significant prolongation partition type turbulence blades.
By favourable design, these two turbulence blades half ones have respectively nut, can tighten turbulence blades half one by it, make on its boundary's wall that is pressed against the downstream.
Preferably, in a burner, be provided with this turbulence blades.By preferred design, in gas turbine, adopt described burner in addition.
Description of drawings
By referring in the explanation of accompanying drawing to embodiment, provide other features of the present invention, characteristics and advantage.
Wherein:
Fig. 1 represents by burner of the present invention with very schematic principle sketch;
Fig. 2 represents to have the combustion chamber sleeve schematic diagram of two fuel gas levels and an oily passage;
Fig. 3 represents to have the turbulence blades schematic diagram of two fuel gas levels;
Fig. 4 represents partition type turbulence blades (cutting the cross section that illustrates by the blade open) schematic diagram in sleeve by the present invention;
Fig. 5 represents partition type turbulence blades (overlooking) schematic diagram in sleeve by the present invention;
Fig. 6 represents to have by the present invention the combustion chamber sleeve schematic diagram of annular adapter and partition type turbulence blades; And
Fig. 7 represents to have the annular adapter top view of partition type turbulence blades.
The specific embodiment
Referring to the Fig. 1 that represents with very schematic principle sketch by burner of the present invention, its explanation burner basic design scheme.
By burner of the present invention, it can for example be used in the gas-turbine combustion chamber with a plurality of same burner combination in case of necessity, comprises an internal control buner system and a main burner system that centers on one heart this control combustion device system.System of not only control combustion device system, and main burner can be by selecting with gaseous state and/or liquid fuel work, for example natural gas or fuel oil.
Control combustion device system comprises an interior oil supply gallery 1, and it is centered on one heart by the interior fuel gas feed path 3 of an annular.Interior fuel gas feed path 3 is centered on one heart by an interior air supply passage or inert substance feed path 5 again.Appropriate ignition system (not expression among the figure) can or be set in this air supply passage in addition.There is an outlet 9 that faces combustion chamber 7 in control combustion device system, in the zone of outlet 9, establishes turbulence blades group 11 in the air supply passage.Fuel gas can be sprayed in the turbulence blades group zone from interior fuel gas feed path 3 by spout 13, or spray in the air supply passage 5 in turbulence blades group upstream.From the oil of oily feed path, can be by atomizer 15, spray in the air of supply in turbulence blades group downstream or in the inert substance of supplying with.
Control combustion device system can be in the known manner as diffusion flame burner oil and/or fuel gas work, and fuel directly sprays in the flame in diffusion flame burner.But also have such possibility, that is, control combustion device system is as premix burner work, and fuel thoroughly mixes with air in premix burner, then mixture is supplied with flame.
Comprise radially externally an air supply passage 17 around the main burner system of control combustion device system, also claim the annular air road, a plurality of turbulence blades 19 of turbulence blades group extend through it.Turbulence blades 19 has the first fuel gas nozzle 21 and the second fuel gas nozzle 23, and gaseous fuel can spray into via in radial air feed path 17 leaked-in airs by them.Can in the air that flows through air supply passage 17, spray into again oil by atomizer 25 in addition.Oil and atomizer although touch upon in the present embodiment, this only should be as the representative of applicable liquid fuel and corresponding nozzle.
Be in the first fuel gas nozzle 21 and the second fuel gas nozzle 23 and atomizer 25 in the turbulence blades 19, by radially being in inner fuel supply system, so-called sleeve 27 fuel supplying.In sleeve 27 interior the first and second annular combustible gas distributors passages 29 and 31 of arranging, they give fuel gas nozzle 21 or 23 supply fuel gas.Turbulence blades 19 and fuel supply system have a fuel flow direction 100.In addition, establish the oil dispenser passage 33 of annular in sleeve 27, it gives atomizer 25 fuel feeding.Combustible gas distributors passage 29,31 and oil dispenser passage 33 is by fuel gas feed path 35,37 or by the corresponding fuel of oily feed path 39 supplies.Fuel gas feed path 35,37 is given combustible gas distributors passage 29,31 fuel supplying.The oily supply pipe 43 that has oneself for oily feed path 39.
Fig. 2 represents to have the fuel sleeve 27 of fuel distributor passage 29 and 31, and it has some that fuel is imported hole in the blade 19.These two fuel distributor passages 29 and 31 substantially parallel layings, and separate by dividing plate 50.
Fig. 3 represents to have turbulence blades 7 schematic diagrams of two fuel gas level B integrated, that can control independently of one another and D.
Turbulence blades 19 has two combustible gas distributors passages 29 independent of each other and 31.One of them has the combustible gas distributors passage 29 of outlet nozzle 21, can for example be used in to spray into medium D, and it is different from the medium (medium B) that the second combustible gas distributors passage 31 sprays into by outlet nozzle 23.Preferably, what these two kinds combustible gas distributors passages 29 and 31 by turbulence blades 19 sprayed into is gaseous medium, and for example a kind of medium is that natural gas and another kind of medium are coal gas.Can spray into a kind of inert substance, for example steam by these outlet nozzles 21 and/or 23 equally when needed.
Known by the present invention, adopt the blade nozzle of dual same design to cause two two cooperations 51 in upper zone and lower region, it causes blade 19 especially no longer can comprise at least one cooperation of adjusting pad 51 adjustment blades oriented by this.Consequently, no longer there is now the point of rotation (fulcrum).Especially can regard nozzle-axis as the point of rotation in this case.Based on a plurality of nozzle-axis and two the cooperation, thereby no longer there is the point of rotation.
Turbulence blades 19 is equipped with the first fuel gas nozzle 21 and another the second additional fuel gas nozzle 23.Wherein, nozzle 21 is supplied with by the first distributor tube 61, and nozzle 23 is supplied with by the second distributor tube 65, and here distributor tube 61,65 is integrated in the turbulence blades 19.
Be designed to by turbulence blades 19 of the present invention now, between the first distributor tube 61 and the second distributor tube 65, be divided into two turbulence blades, half 19a of, 19b (Fig. 4).The advantage of doing like this is that these nozzles can be by spout 21 and 23 independent controls.Can implement thus different " classification (staging) ".Thereby also can distinguish control channel 31 and 29.This is favourable for also plaing a part service life, because also can control the thermic load of these two passages 31 and 29 now.This is changing to full load from sub-load, and when changing from full load to sub-load conversely, all is particularly advantageous.Have two blades of 51 of cooperating and compare with one, the faster and considerably cheaper of the manufacturing of partition type blade 19a, 19b.In addition, the blades oriented of these two turbulence blades half 19a of, 19b can be undertaken by adjusting pad.
Turbulence blades half 19a of, 19b have a kind of cooperation at the outer boundary wall 17b of air supply passage 17 in addition, that is to say, so-called cooperation plug 90a, a 90b and slide 85a, a 85b are arranged, and it is installed in the sleeve 27 itself.By cooperating plug 90a, 90b and slide 85a, a 85b, these two turbulence blades half 19a of, 19b can separate thermal expansion now, reduce equally thus stress.Outer boundary wall 17b at air supply passage 17 screws these two turbulence blades half 19a of, 19b with nut 86a, 86b (Fig. 5), is pressed against on this outer boundary wall 17b.
Sleeve 27 can also comprise a supply pipe 55 (Fig. 6 and 7), it is connected with the 19a of one of turbulence blades half one (19b) in the downstream, and comprise an annular adapter 60, wherein, supply pipe 55 is connected with annular adapter 60 in the upstream, here, annular adapter 60 is seen and is connected to fuel distributor passage 31 (or 29) upstream along flowing to 100.Therefore can say one of distributor passage 29 or 31 is designed to supply pipe 55.
Supply pipe 55 imports distributor tube 61 (or 65) in the downstream.Supply pipe 55 is connected with annular adapter 60 (Fig. 5) in the upstream.Here, annular adapter 60 is seen along the flow direction and is connected to fuel distributor passage 31 (or 29) upstream.Make thus original fuel distributor passage 31 (or 29) be parallel to supply pipe 55.Annular adapter 60 is by 75 supplies of independent pipe joint.Fuel distributor passage 31 (or 29) originally is by another passage 80 supplies.So these two fuel gas guiding channels, that is supply pipe 55 and annular adapter 60 and original fuel distributor passage 31 (or 29) are by spatially decoupling of the present invention.Annular adapter 60 plays a part as follows: it is removed heavily stressed in the sleeve 27 and stress is distributed on member equably.Thus by reducing the stress elimination to the harm of structure space.
In order to reach further reduction stress, the dividing plate 50 that fuel distributor passage 31 (or 29) and supply pipe 55 are separated is designed to flexible.Here dividing plate 50 can be with a kind of elastomeric material manufacturing.Additional or different therewith, dividing plate 50 also can cause elasticity and thereby counteracting stress by corresponding geometry designs.This for example can cause by the dividing plate 50 of bending or waveform.

Claims (10)

1. a turbulence blades (19), comprise first a fuel gas nozzle (21) and the second fuel gas nozzle (23) that adds in addition, wherein, the first nozzle (21) is supplied with by the first distributor tube (61), and second nozzle (23) is supplied with by the second distributor tube (65), here, distributor tube (61,65) is integrated in the turbulence blades (19), it is characterized by: turbulence blades (19) is designed to, and is divided into two turbulence blades half ones (19a, 19b) between the first distributor tube (61) and the second distributor tube (65).
2. according to turbulence blades claimed in claim 1 (19), it is characterized by, described two turbulence blades half ones (19a, 19b) can separately make.
3. according to claim 1 or 2 described turbulence blades (19), it is characterized by, described turbulence blades half one (19a, 19b) is installed in the annular air channel (17) of supplying with combustion air, and has a flow direction (100) in when work, and in the upstream respectively with the first fuel distributor passage (29) be connected fuel distributor passage (31) and be connected, wherein, the first and second fuel distributor passages (29,31) are arranged in the center fuel feedway (27).
4. according to claim 1 or 2 described turbulence blades (19), it is characterized by, described turbulence blades half one (19a, 19b) is installed in the annular air channel (17) of supplying with combustion air, described annular air channel is around center fuel feedway (27), wherein, the first fuel nozzle (21) is supplied with by the first fuel distributor feedway (29) in center fuel feedway (27), and the second fuel nozzle (23) is supplied with by the second fuel distributor passage (31) in center fuel feedway (27).
5. according to turbulence blades claimed in claim 4 (19), it is characterized by, fuel distributor feedway (29) has a flow direction (100) and comprises supply pipe (55), this supply pipe is connected with one of turbulence blades (19a, 19b) in the downstream, and comprise annular adapter (60), wherein, supply pipe (55) is connected with this annular adapter (60) in the upstream, wherein, annular adapter (60) is seen along the flow direction and is connected to fuel distributor passage (31) upstream.
6. according to the described turbulence blades of one of claim 2 to 5 (19), it is characterized by, described two turbulence blades half ones (19a, 19b) have in the downstream and cooperate plug (90a, 90b) and have slide (85a, 85b) in the upstream.
7. according to turbulence blades claimed in claim 6 (19), it is characterized by, described slide (85a, 85b) is at least part of stretching in the center fuel feedway (27) in the upstream.
8. according to the described turbulence blades of one of claim 2 to 7 (19), it is characterized by, described two turbulence blades half ones (19a, 19b) have respectively nut (86a, 86b), can tighten turbulence blades half one (19a, 19b) by described nut, make on its boundary's wall (17b) that is pressed against annular air channel (17) downstream.
9. a burner has according to the described turbulence blades of one of all claims in prostatitis (19).
10. a gas turbine has at least one according to burner claimed in claim 9.
CN201080048386.3A 2009-08-26 2010-08-23 Turbulence blades, burner and gas turbine Expired - Fee Related CN102906500B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102009038845A DE102009038845A1 (en) 2009-08-26 2009-08-26 Swirl vane, burner and gas turbine
DE102009038845.1 2009-08-26
PCT/EP2010/062214 WO2011023648A2 (en) 2009-08-26 2010-08-23 Swirl blade, burner and gas turbine

Publications (2)

Publication Number Publication Date
CN102906500A true CN102906500A (en) 2013-01-30
CN102906500B CN102906500B (en) 2016-03-09

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CN201080048386.3A Expired - Fee Related CN102906500B (en) 2009-08-26 2010-08-23 Turbulence blades, burner and gas turbine

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EP (1) EP2470833A2 (en)
CN (1) CN102906500B (en)
DE (1) DE102009038845A1 (en)
RU (1) RU2535433C2 (en)
WO (1) WO2011023648A2 (en)

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CN106461224A (en) * 2013-03-04 2017-02-22 西门子公司 Pre-film liquid fuel cartridge
CN109026175A (en) * 2018-08-31 2018-12-18 中国航发动力股份有限公司 A kind of spoiler assembling structure and its assembly method
CN112189113A (en) * 2018-05-25 2021-01-05 库珀斯解决方案有限公司 Fuel nozzle system
CN114110662A (en) * 2021-11-25 2022-03-01 同济大学 Low-nitrogen combustion chamber of gas turbine

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KR20150039763A (en) * 2012-08-06 2015-04-13 지멘스 악티엔게젤샤프트 Local improvement of the mixture of air and fuel in burners comprising swirl generators having blade ends that are crossed in the outer region
WO2015067482A1 (en) * 2013-11-08 2015-05-14 Siemens Aktiengesellschaft Gas turbine burner having separately controllable fuel stages in pilot burner swirl vanes
DE102015206227A1 (en) * 2015-04-08 2016-10-13 Siemens Aktiengesellschaft burner arrangement
EP3301368A1 (en) 2016-09-28 2018-04-04 Siemens Aktiengesellschaft Swirler, combustor assembly, and gas turbine with improved fuel/air mixing

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106461224A (en) * 2013-03-04 2017-02-22 西门子公司 Pre-film liquid fuel cartridge
CN106461224B (en) * 2013-03-04 2019-07-05 西门子公司 The combusting room device of gas-turbine unit
CN112189113A (en) * 2018-05-25 2021-01-05 库珀斯解决方案有限公司 Fuel nozzle system
CN109026175A (en) * 2018-08-31 2018-12-18 中国航发动力股份有限公司 A kind of spoiler assembling structure and its assembly method
CN109026175B (en) * 2018-08-31 2020-12-29 中国航发动力股份有限公司 Spoiler assembling structure and assembling method thereof
CN114110662A (en) * 2021-11-25 2022-03-01 同济大学 Low-nitrogen combustion chamber of gas turbine
CN114110662B (en) * 2021-11-25 2023-02-10 同济大学 Low-nitrogen combustion chamber of gas turbine

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RU2535433C2 (en) 2014-12-10
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EP2470833A2 (en) 2012-07-04
DE102009038845A1 (en) 2011-03-03

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