CN104534515A - Combustion chamber head structure of gas turbine - Google Patents

Combustion chamber head structure of gas turbine Download PDF

Info

Publication number
CN104534515A
CN104534515A CN201410727617.3A CN201410727617A CN104534515A CN 104534515 A CN104534515 A CN 104534515A CN 201410727617 A CN201410727617 A CN 201410727617A CN 104534515 A CN104534515 A CN 104534515A
Authority
CN
China
Prior art keywords
jet
nozzle
chamber
swirl
cylinder
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201410727617.3A
Other languages
Chinese (zh)
Other versions
CN104534515B (en
Inventor
吕煊
方子文
李珊珊
王绥德
陈伟
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
China United heavy-duty gas turbine technology Co., Ltd.
Original Assignee
Beijing Huatsing Gas Turbine & Igcc Technology Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Beijing Huatsing Gas Turbine & Igcc Technology Co Ltd filed Critical Beijing Huatsing Gas Turbine & Igcc Technology Co Ltd
Priority to CN201410727617.3A priority Critical patent/CN104534515B/en
Publication of CN104534515A publication Critical patent/CN104534515A/en
Application granted granted Critical
Publication of CN104534515B publication Critical patent/CN104534515B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Abstract

The invention relates to the technical field of combustion chambers of gas turbines and discloses a combustion chamber head structure of the gas turbine. The combustion chamber head structure of the gas turbine comprises a head end plate, a central nozzle arranged at the head end plate, and a plurality of jet nozzle rings around the central nozzle; a swirl nozzle ring is arranged between any two adjacent jet nozzle rings; each swirl nozzle ring comprises a plurality of swirl nozzle modules arranged at intervals; the central nozzle is a swirl nozzle module; each jet nozzle ring comprises an annular jet nozzle or a plurality of jet nozzle modules arrayed at intervals. The combustion chamber head structure of the gas turbine is provided with a plurality of swirl nozzle rings and jet nozzle rings, distributed flame is formed to obtain lifted uniform flame when burning, the combustion mode of the combustion chamber is located at a distributed flame zone, and the pollutant emission of the whole combustion chamber is effectively lowered.

Description

Gas-turbine combustion chamber head construction
Technical field
The present invention relates to gas-turbine combustion chamber technical field, particularly relate to a kind of gas-turbine combustion chamber head construction.
Background technology
For industrial heavy gas turbine, between many decades, developing goal is always higher combustor exit mean temperature (demarcating gas turbine technology grade) and more low stain thing discharge; Above-mentioned technical indicator and combustion chamber are closely related and self is conflicting, higher combustor exit mean temperature means that more multi fuel participates in combustion process, burning average indoor temperature is higher, and as the nitrogen oxide of combustion chamber major pollutants and combustion chamber thermal procession closely related.The basic function of gas-turbine combustion chamber be in the confined space high strength by organizing fuel and air to flow concurrent biochemical reaction, be heat energy thus promote turbine acting in combustion gas by chemical energy in fuel.Its core is the reciprocation of turbulent mixing process and chemical reaction kinetics process.Existing combustion chamber adopts swirl-flow premixed structure, and along with the further rising of combustion chamber mean outlet temperature, this kind of head of combustion chamber structure is for control combustion room discharged nitrous oxides limited use.The nineties in 20th century is known with now up-to-date combustion chamber product more in the world, its outlet mean temperature increase about 200 DEG C, although combustion chamber is through series of optimum and improvement, but the emission level of its nitrogen oxide maintain an equal level even slightly raise, which illustrate current combustion room project organization for future more high parameter combustion chamber time, its limited potential, is faced with the risk that can not meet discharge standard.
Summary of the invention
(1) technical problem that will solve
The object of this invention is to provide a kind of gas-turbine combustion chamber head construction that effectively can reduce discharged nitrous oxides.
(2) technical scheme
In order to solve the problems of the technologies described above, the central nozzle of the described head end plate that the invention provides a kind of gas-turbine combustion chamber head construction, comprise head end plate, is arranged on and the multiple jet nozzle circles be looped around around described central nozzle; A swirl nozzle circle is provided with between the described jet nozzle circle of arbitrary neighborhood two; Each described swirl nozzle circle comprises multiple swirl nozzle module be intervally arranged; Described central nozzle is also a swirl nozzle module; Often enclose described jet nozzle circle and comprise an annular jet nozzle or multiple spaced jet nozzle module.
Wherein, described swirl nozzle module comprises whirl cylinder, eddy flow cartridge and multiple swirl vane, and described eddy flow cartridge is arranged on the center of described whirl cylinder; Multiple described swirl vane is arranged on described eddy flow cartridge; Each described swirl vane is provided with multiple fuel swirl hole, and described fuel swirl hole is communicated with eddy flow cartridge.
Wherein, multiple described swirl vane is evenly arranged along the circumference of described eddy flow cartridge.
Wherein, the center of described jet nozzle circle and the center of described central nozzle coincide.
Further, described jet nozzle module comprises jet cartridge and jet cylinder, and one end of described jet cylinder is connected with described jet cartridge, and the other end is provided with outlet end plate; Be provided with inlet baffle in described jet cylinder, described jet cylinder is separated into front chamber and rear chamber by described inlet baffle, and the sidewall of described front chamber is provided with air intake; Described outlet end plate is provided with air-spray hole and fuel jet hole, and described fuel jet hole is communicated with rear chamber by little fluidic conduit.
Wherein, the cross section of described jet cylinder is rectangle, circle, fan-shaped or oval.
Wherein, described air intake, air-spray hole and fuel jet hole are multiple.
Wherein, the diameter in described air-spray hole and fuel jet hole is 1 ~ 1.5mm.
Further, described annular jet nozzle comprises interior jet cylinder, outer jet cylinder and jet cartridge, and described interior jet cylinder and outer jet cylinder are arranged with one heart; Jet chamber is formed between described interior jet cylinder and outer jet cylinder; Described jet chamber is provided with front apron, middle baffle plate and backboard, forms front chamber and rear chamber; Described jet cartridge is communicated with described rear chamber; The sidewall of described front chamber is provided with air intake; Described front apron is provided with air-spray hole and fuel jet hole, and described fuel jet hole is communicated with rear chamber by little fluidic conduit.
(3) beneficial effect
Gas-turbine combustion chamber head construction provided by the invention, head of combustion chamber arranges multiple swirl nozzle circle and jet nozzle circle, distributed flame is formed during burning, obtain the overall uniform flame of a lifting, make combustion chambers burn pattern be in distribution flame zone, effectively reduce the pollutant emission of whole combustion chamber.
Accompanying drawing explanation
Fig. 1 is the structural perspective of the embodiment of the present invention 1;
Fig. 2 is the front elevational schematic of the embodiment of the present invention 1;
Fig. 3 is the sectional view of the embodiment of the present invention 1;
Fig. 4 is the sectional view of the jet nozzle module of the embodiment of the present invention 1;
Fig. 5 is the front elevational schematic of the another kind of embodiment of the embodiment of the present invention 1;
Fig. 6 is the front elevational schematic of the embodiment of the present invention 2;
Fig. 7 is the sectional view of the embodiment of the present invention 2.
In figure, 1: head end plate; 10: central nozzle; 20: jet nozzle circle; 30: swirl nozzle circle; 11: swirl nozzle module; 12: jet nozzle module; 110: whirl cylinder; 111: eddy flow cartridge; 112: swirl vane; 113: fuel swirl hole; 120: jet cylinder; 121: air intake; 122: jet cartridge; 123: inlet baffle; 124: little fluidic conduit; 125: outlet end plate; 126: fuel jet hole; 127: air-spray hole; 128: rear chamber; 129: front chamber; 13: annular jet module; 130: interior jet cylinder; 131: jet cartridge; 132: front apron; 133: middle baffle plate; 134: backboard; 135: air intake; 136: rear chamber; 137: front chamber; 138: little fluidic conduit; 139: outer jet cylinder; 1321: air-spray hole; 1322: fuel jet hole.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following instance for illustration of the present invention, but is not used for limiting the scope of the invention.
Embodiment 1:
Shown in 4, gas-turbine combustion chamber head construction of the present invention, comprises head end plate 1, central nozzle 10, jet nozzle circle 20 and swirl nozzle circle 30.Head end plate 1 is provided with multiple fuel air passage, and central nozzle 10, jet nozzle circle 20 and swirl nozzle circle 30 are installed on head end plate 1, and with fuel air channel connection, outside provide fuel for fuel apparatus by fuel air passage.Jet nozzle circle 20 is multiple, and multiple jet nozzle circle 20 is looped around around central nozzle 10, and the center of the Center-to-Center nozzle 10 of jet nozzle circle 20 coincides.Namely multiple jet nozzle circle 20 is arranged with one heart, and central nozzle 10 is arranged on the center of innermost circle jet nozzle circle 20.Be provided with a swirl nozzle circle 30 between arbitrary neighborhood two jet nozzle circles 20, make jet nozzle circle 20 and swirl nozzle circle 30 staggered on head end plate 1, and the nozzle circle of outmost turns is jet nozzle circle 20.Each swirl nozzle circle 30 comprises multiple swirl nozzle module 11 be intervally arranged.Central nozzle 10 is also a swirl nozzle module 11.In the present embodiment, jet nozzle circle 20 comprises multiple jet nozzle module 12 be intervally arranged.
Further, swirl nozzle module 11 comprises whirl cylinder 110, eddy flow cartridge 111 and multiple swirl vane 112, and eddy flow cartridge 111 inserts from the rear end of whirl cylinder 110, and is arranged on the center of whirl cylinder 110; The front end of eddy flow cartridge 111 is closed, and rear end is used for being arranged on head end plate 1.Multiple swirl vane 112 is arranged on eddy flow cartridge 111, and preferably, swirl vane 112 is arranged between the inwall of eddy flow cartridge 111 and whirl cylinder 110.Each swirl vane 112 is provided with multiple fuel swirl hole 113, and fuel swirl hole 113 is communicated with eddy flow cartridge 111.In the present embodiment, swirl vane 112 is 8, and 8 swirl vanes 112 are evenly arranged along the circumference of eddy flow cartridge 111.Preferably, in order to control the air mass flow in whirl cylinder 110, cowling panel or restriction orifice is provided with in the rear end of whirl cylinder 110.
Further, each jet nozzle module 12 comprises jet cartridge 122 and jet cylinder 120.The cross section of jet cylinder 120 is circular.One end of jet cylinder 120 is connected with one end of jet cartridge 122, and the other end is provided with outlet end plate 125.Jet cartridge 122 rear end is connected with head end plate 1.Fuel used in the present invention is natural gas or natural gas-hydrogen mixture fuel.Inlet baffle 123 is provided with in jet cylinder 120.Jet cylinder 120 is separated into front chamber 129 and rear chamber 128 by inlet baffle 123, and the sidewall of front chamber 129 is provided with air intake 121; Outlet end plate 125 is provided with air-spray hole 127 and fuel jet hole 126, and fuel jet hole 126 is communicated with rear chamber 128 by little fluidic conduit 124.Fuel feeds from jet cartridge 122 to rear chamber 128, and is penetrated from fuel jet hole 126 by little fluidic conduit 124, and air enters front chamber 129 from air intake 121, and penetrates from air-spray hole 127.Fuel injection is injected in each jet nozzle module with air and separates, need could mix from the position away from nozzle head, make combustion zone away from nozzle head region, decrease the cooling structure design of nozzle head, save film-cooled heat, ensure that more air can participate in burning, reduce the generation of nitrogen oxide, thus meet more high-grade combustion chamber demand; Fuel injection is simultaneously injected in each nozzle module with air and separates, and needs certain region to carry out blending in nozzle module downstream, and this segment distance reduces the possibility that tempering occurs greatly.When fuel, swirl nozzle module 11 fuel quantity accounts for 10 ~ 15% of whole chamber fuel amount, and the eddy flow fuel ratio of whole combustion chamber is lower, makes the equivalent proportion of the eddy flow mixture of whole combustion chamber be unlikely to too high, further control polluted articles discharge.
Preferably, air intake 121, air-spray hole 127 and fuel jet hole 126 are multiple, and the diameter in air-spray hole 127 and fuel jet hole 126 is 1 ~ 1.5mm.
The cross section of jet cylinder 120, can also as shown in Figure 5 fan-shaped except can be except circle, and in addition, the cross section that also can be can also be rectangle or ellipse.
When using gas-turbine combustion chamber head construction of the present invention, the partial air entering combustion chamber enters jet nozzle module 12 inside from air intake 121, the air-spray hole 127 exported end plate 125 from jet nozzle module 12 sprays, part of fuel enters jet nozzle module 12 inside from jet cartridge 122 and enters little fluidic conduit 124 by the hole fuel inlet baffle plate 123 and penetrate from the fuel jet hole 126 the outlet end plate 125 of jet nozzle module 12, and air becomes high-speed jet mixture with fuel in jet nozzle module 12 mixed downstream; Remaining part of fuel and air enter swirl nozzle module 11 and form rotational flow air fuel mixture, play igniting and stabilize the flame, its high-temperature flue gas formed is used for lighting high-speed jet mixture on the one hand, on the other hand dilution blending is carried out to high-speed jet mixture, integral combustion room flame front is disperseed, makes combustion chambers burn pattern be in distribution flame zone, reduce the generation of nitrogen oxide, the pollutant emission of the whole combustion chamber of effective reduction, reduces the risk that hot acoustic shock is swung.
Embodiment 2:
The present embodiment is substantially the same manner as Example 1, and institute's difference is, as shown in Figures 6 and 7, in the present embodiment, jet nozzle circle comprises an annular jet nozzle 13.Annular jet nozzle 13 comprises interior jet cylinder 130, outer jet cylinder 139 and jet cartridge 131, interior jet cylinder 130 and outer jet cylinder 139 are arranged with one heart, the external diameter of interior jet cylinder 130 is less than the internal diameter of outer jet cylinder 139, jet chamber is formed between interior jet cylinder 130 and outer jet cylinder 139, front apron 132 is provided with in jet chamber, middle baffle plate 133 and backboard 134, jet chamber between interior jet cylinder 130 and outer jet cylinder 139 is divided into front chamber 137 by front apron 132 and middle baffle plate 133, jet chamber between interior jet cylinder 130 and outer jet cylinder 139 is divided into rear chamber 136 by middle baffle plate 133 and backboard 134.The front end of jet cartridge 131 is communicated with rear chamber 136, and the rear end of jet cartridge 131 is used for being arranged on head end plate 1, with the fuel air channel connection be arranged on head end plate 1.The sidewall of front chamber 137 is provided with air intake 135, with reference to shown in Fig. 7, at interior jet cylinder 130 and outer jet cylinder 139, air intake 135 is set, air intake 135 is communicated with front chamber 137, air in combustion chamber flow in front chamber 137 by air intake 135, the quantity of air intake 135 is multiple, and multiple air intake 135 is evenly distributed.Front apron 132 is provided with air-spray hole 1321 and fuel jet hole 1322, and fuel jet hole 1322 is communicated with rear chamber 136 by little fluidic conduit 138.Fuel flows to rear chamber 136 from jet cartridge 131, then by rear chamber 136 by after little fluidic conduit 138, penetrates from fuel jet hole 1322, improves the effluxvelocity of fuel.Air flow into front chamber 137 from air intake 135, then penetrates from the air-spray hole 1321 of front apron 132.
When burning, pass into combustion gas from the fuel air passage of head end plate respectively to eddy flow cartridge and jet cartridge.In swirl nozzle module, air enters in whirl cylinder by the rear end of whirl cylinder, and fuel sprays from the fuel swirl hole of swirl vane, forms stable swirl flame.Fuel enters rear chamber by jet cartridge, and sprayed from fuel jet hole by little fluidic conduit, form fuel at a high speed to spray, simultaneously, air enters front chamber from air intake, and by the ejection at a high speed of air-spray hole, fuel jet and air-spray just can be mixed to form burning gases from jet nozzle larger distance, and light formation jet flame.The combustion flame of annular jet nozzle, away from nozzle head, decreases the cooling structure of nozzle head, saves film-cooled heat, ensures that more air participates in burning, reduces the generation of nitrogen oxide.
Gas-turbine combustion chamber head construction of the present invention, be provided with multiple swirl nozzle circle and jet nozzle circle, during burning, form distributed flame, obtain the overall uniform flame of a lifting, make combustion chambers burn pattern be in distribution flame zone, effectively reduce the pollutant emission of whole combustion chamber.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.

Claims (9)

1. a gas-turbine combustion chamber head construction, is characterized in that, comprises head end plate, is arranged on the central nozzle of described head end plate and is looped around the multiple jet nozzle circles around described central nozzle; A swirl nozzle circle is provided with between the described jet nozzle circle of arbitrary neighborhood two; Each described swirl nozzle circle comprises multiple swirl nozzle module be intervally arranged; Described central nozzle is also a swirl nozzle module; Often enclose described jet nozzle circle and comprise an annular jet nozzle or multiple spaced jet nozzle module.
2. gas-turbine combustion chamber head construction as claimed in claim 1, it is characterized in that, described swirl nozzle module comprises whirl cylinder, eddy flow cartridge and multiple swirl vane, and described eddy flow cartridge is arranged on the center of described whirl cylinder; Multiple described swirl vane is arranged on described eddy flow cartridge; Each described swirl vane is provided with multiple fuel swirl hole, and described fuel swirl hole is communicated with eddy flow cartridge.
3. gas-turbine combustion chamber head construction as claimed in claim 2, it is characterized in that, multiple described swirl vane is evenly arranged along the circumference of described eddy flow cartridge.
4. gas-turbine combustion chamber head construction as claimed in claim 1, it is characterized in that, the center of described jet nozzle circle and the center of described central nozzle coincide.
5. the gas-turbine combustion chamber head construction as described in any one of Claims 1-4, is characterized in that, described jet nozzle module comprises jet cartridge and jet cylinder, and one end of described jet cylinder is connected with described jet cartridge, and the other end is provided with outlet end plate; Be provided with inlet baffle in described jet cylinder, described jet cylinder is separated into front chamber and rear chamber by described inlet baffle, and the sidewall of described front chamber is provided with air intake; Described outlet end plate is provided with air-spray hole and fuel jet hole, and described fuel jet hole is communicated with rear chamber by little fluidic conduit.
6. gas-turbine combustion chamber head construction as claimed in claim 5, is characterized in that, the cross section of described jet cylinder is rectangle, circle, fan-shaped or oval.
7. gas-turbine combustion chamber head construction as claimed in claim 5, it is characterized in that, described air intake, air-spray hole and fuel jet hole are multiple.
8. gas-turbine combustion chamber head construction as claimed in claim 5, it is characterized in that, the diameter in described air-spray hole and fuel jet hole is 1 ~ 1.5mm.
9. the gas-turbine combustion chamber head construction as described in any one of Claims 1-4, is characterized in that, described annular jet nozzle comprises interior jet cylinder, outer jet cylinder and jet cartridge, and described interior jet cylinder and outer jet cylinder are arranged with one heart; Jet chamber is formed between described interior jet cylinder and outer jet cylinder; Described jet chamber is provided with front apron, middle baffle plate and backboard, forms front chamber and rear chamber; Described jet cartridge is communicated with described rear chamber; The sidewall of described front chamber is provided with air intake; Described front apron is provided with air-spray hole and fuel jet hole, and described fuel jet hole is communicated with rear chamber by little fluidic conduit.
CN201410727617.3A 2014-12-03 2014-12-03 Gas-turbine combustion chamber head construction Active CN104534515B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410727617.3A CN104534515B (en) 2014-12-03 2014-12-03 Gas-turbine combustion chamber head construction

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410727617.3A CN104534515B (en) 2014-12-03 2014-12-03 Gas-turbine combustion chamber head construction

Publications (2)

Publication Number Publication Date
CN104534515A true CN104534515A (en) 2015-04-22
CN104534515B CN104534515B (en) 2018-04-20

Family

ID=52850094

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410727617.3A Active CN104534515B (en) 2014-12-03 2014-12-03 Gas-turbine combustion chamber head construction

Country Status (1)

Country Link
CN (1) CN104534515B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110631049A (en) * 2019-10-12 2019-12-31 中国科学院工程热物理研究所 Soft combustion chamber of gas turbine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102032597A (en) * 2010-11-29 2011-04-27 北京航空航天大学 Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe
CN103292355A (en) * 2012-02-28 2013-09-11 株式会社日立制作所 Gas turbine combustor and method for operating same
JP5372815B2 (en) * 2010-03-17 2013-12-18 株式会社日立製作所 Gas turbine combustor
CN203586283U (en) * 2013-07-10 2014-05-07 辽宁省燃烧工程技术中心(有限公司) Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel
CN203671658U (en) * 2013-12-11 2014-06-25 中航商用航空发动机有限责任公司 Combustion chamber of combustion gas turbine and combustion gas turbine with same
CN203757765U (en) * 2012-12-10 2014-08-06 通用电气公司 Burner and gas turbine
CN204404241U (en) * 2014-12-03 2015-06-17 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Gas-turbine combustion chamber head construction

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5372815B2 (en) * 2010-03-17 2013-12-18 株式会社日立製作所 Gas turbine combustor
CN102032597A (en) * 2010-11-29 2011-04-27 北京航空航天大学 Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe
CN103292355A (en) * 2012-02-28 2013-09-11 株式会社日立制作所 Gas turbine combustor and method for operating same
CN203757765U (en) * 2012-12-10 2014-08-06 通用电气公司 Burner and gas turbine
CN203586283U (en) * 2013-07-10 2014-05-07 辽宁省燃烧工程技术中心(有限公司) Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel
CN203671658U (en) * 2013-12-11 2014-06-25 中航商用航空发动机有限责任公司 Combustion chamber of combustion gas turbine and combustion gas turbine with same
CN204404241U (en) * 2014-12-03 2015-06-17 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Gas-turbine combustion chamber head construction

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110631049A (en) * 2019-10-12 2019-12-31 中国科学院工程热物理研究所 Soft combustion chamber of gas turbine

Also Published As

Publication number Publication date
CN104534515B (en) 2018-04-20

Similar Documents

Publication Publication Date Title
US9752781B2 (en) Flamesheet combustor dome
US8171735B2 (en) Mixer assembly for gas turbine engine combustor
TW425467B (en) Burner for use in a combustion system and method of premixing fuel and air in the burner
US5816049A (en) Dual fuel mixer for gas turbine combustor
CN102175043B (en) Gas turbine engine combustor can with trapped vortex cavity
US7757491B2 (en) Fuel nozzle for a gas turbine engine and method for fabricating the same
US5511375A (en) Dual fuel mixer for gas turbine combustor
CN100510540C (en) Gas turbine combustor
CA2820071C (en) Axial swirler for a gas turbine burner
EP1543272B1 (en) Turbine engine fuel nozzle
CN105051458B (en) Burner and gas turbine
US6752620B2 (en) Large scale vortex devices for improved burner operation
CN1878986B (en) Device for stabilizing combustion in gas turbine engines
CN101275750B (en) Radial swirler turning zone direct injection premixing and prevapourising low pollution burning chamber
KR101523938B1 (en) Method for controlling combustion in a gas trubine engine and cumbustor for a gas turbine combustion system
CN104114944B (en) Fuel is sprayed into the cyclone line of rabbet joint with inclined fuel injection manner
CN103388838B (en) The system and method with the multi-tube fuel nozzle with differential flow
EP2500641A1 (en) Recirculating product injection nozzle
US5596873A (en) Gas turbine combustor with a plurality of circumferentially spaced pre-mixers
CN102032598B (en) Circumferentially graded low-pollution combustion chamber with multiple middle spiral-flow flame stabilizing stages
EP2500654B1 (en) Combustion burner for gas turbine
EP2383516A2 (en) Pocketed air and fuel mixing tube
JP2008292139A (en) Combustor and fuel supply method of combustor
US20070272201A1 (en) Combustion Apparatus and Combustion Method
US8739546B2 (en) Gas turbine combustor with quench wake control

Legal Events

Date Code Title Description
PB01 Publication
C06 Publication
SE01 Entry into force of request for substantive examination
C10 Entry into substantive examination
GR01 Patent grant
GR01 Patent grant
PP01 Preservation of patent right

Effective date of registration: 20190820

Granted publication date: 20180420

Effective date of registration: 20190820

Granted publication date: 20180420

PP01 Preservation of patent right
PD01 Discharge of preservation of patent

Date of cancellation: 20191230

Granted publication date: 20180420

PD01 Discharge of preservation of patent
TR01 Transfer of patent right

Effective date of registration: 20200116

Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing

Patentee after: China United heavy-duty gas turbine technology Co., Ltd.

Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10

Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd.

TR01 Transfer of patent right