CN103486591A - Tempering-proof nozzle connecting section assembly of combustor of combustion gas turbine - Google Patents
Tempering-proof nozzle connecting section assembly of combustor of combustion gas turbine Download PDFInfo
- Publication number
- CN103486591A CN103486591A CN201310397606.9A CN201310397606A CN103486591A CN 103486591 A CN103486591 A CN 103486591A CN 201310397606 A CN201310397606 A CN 201310397606A CN 103486591 A CN103486591 A CN 103486591A
- Authority
- CN
- China
- Prior art keywords
- passage
- assembly
- linkage section
- fuel nozzle
- combustion chamber
- 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
Links
- 239000000567 combustion gas Substances 0.000 title abstract 3
- 239000000446 fuel Substances 0.000 claims abstract description 76
- 238000002485 combustion reaction Methods 0.000 claims description 33
- 238000001816 cooling Methods 0.000 claims description 20
- 230000004323 axial length Effects 0.000 claims description 11
- 239000003380 propellant Substances 0.000 claims description 10
- 239000007921 spray Substances 0.000 claims description 10
- 238000005496 tempering Methods 0.000 abstract description 12
- 238000011144 upstream manufacturing Methods 0.000 abstract description 9
- 239000007789 gas Substances 0.000 description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 9
- 230000002411 adverse Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
Images
Abstract
The invention discloses a tempering-proof nozzle connecting section assembly of a combustor of a combustion gas turbine and belongs to the structural design of the combustor of the combustion gas turbine. The nozzle connecting section assembly comprises a fuel nozzle assembly and a fuel nozzle connecting section, wherein the fuel nozzle connecting section is located outside the fuel nozzle assembly; the fuel nozzle assembly comprises a whirlcone, a fuel injecting device and a nozzle assembly centre body; the fuel nozzle connecting section comprises a cylindrical channel, a contracted channel and an expanded channel; the axial position of a throat at the connecting part of the contracted channel and the expanded channel is arranged at the downstream part of the axial position at the tail end of the nozzle assembly centre body. A special structural form is adopted at the fuel nozzle connecting section, and especially, the structure of an inner channel of the fuel nozzle connecting section is improved; when tempering happens at the downstream part, the fuel nozzle assembly at the upstream part can be effectively protected and prevented from being burned out.
Description
Technical field
The present invention relates to the gas turbine structure design, relate in particular to the anti-backfire type nozzle linkage section assembly of gas-turbine combustion chamber.
Background technology
Fig. 1 is a typical chamber structure in prior art, and gas turbine 10 comprises that a compressor 12(partly marks), a plurality of combustion chambers (only marking one in figure) and a turbine (representing with turbine blade 16 in figure).Turbine 16 and compressor 12 have a common axis.The air entered by compressor 12 is through pressurization, and adverse current enters combustion chamber 14, and burning is also cooling along journey, finally enters turbine 16.
As mentioned above, gas turbine 10 comprises a plurality of combustion chambers 14 that are positioned at around gas turbine.Each combustion chamber 14 comprises an end-cap assembly 30, and this end-cap assembly 30 comprises fuel feed pipe and corresponding valve etc.; Be connected to a plurality of fuel nozzle assemblies 32 on end-cap assembly 30, described a plurality of fuel nozzle assemblies 32 are arranged in a circular group round the longitudinal axis of combustion chamber, comprise cyclone 33 and propellant spray device 35 on each fuel nozzle assembly 32; Limit the burner inner liner calotte assembly 42 of each fuel nozzle assembly 32 interior air current flow, this assembly has a plurality of fuel nozzle linkage sections 54 keeps apart each fuel nozzle assembly 32; The water conservancy diversion lining 34 that burner inner liner 38 and burner inner liner are outer; The water conservancy diversion lining 40 that changeover portion 18 and changeover portion are outer, the outer water conservancy diversion lining 40 of described changeover portion has the Cooling Holes 44 of impact.
As mentioned above in structure, impact Cooling Holes 44 on the water conservancy diversion lining 40 that air-flow in gas turbine 10 passes outside changeover portion through compressor 12 along the direction of arrow and enter the circular passage that the water conservancy diversion lining 40 outside changeover portion 18 and changeover portion forms, adverse current enters the circular passage that the water conservancy diversion lining 34 outside burner inner liner 38 and burner inner liner forms, the circular passage that the outer water conservancy diversion lining 34 of burner inner liner calotte assembly 42 and burner inner liner of flowing through forms, regional flow divert through end-cap assembly 30 with the front end of burner inner liner calotte assembly 42, enter the little circular passage of fuel nozzle linkage section 54 compositions of each fuel nozzle assembly 32 and burner inner liner calotte assembly 42, final by cyclone 33 and propellant spray device 35, through fuel nozzle linkage section 54, fuel is mixed with air and enters burner inner liner 38.
General, head of combustion chamber comprises that a plurality of diffusions or premixed fuel nozzle assembly 32 are centered around the combustion chamber longitudinal axis and line up a circular group.These fuel nozzle assembly 32 front ends are connected with head of combustion chamber end-cap assembly 30, and rear end is stretched in the corresponding fuel nozzle linkage section 54 of burner inner liner calotte assembly 42.The end of each fuel nozzle assembly 32, in corresponding fuel nozzle linkage section 54, and approaches the outlet of corresponding fuel nozzle linkage section 54, and the outlet of fuel nozzle linkage section 54 directly is connected with the combustion zone of combustion chamber flame drum 38.
The fuel nozzle linkage section more than 54 of fuel nozzle assembly 32 of the prior art adopts the column type interior wall construction, in the cylindrical structure of described fuel nozzle linkage section 54, fuel and air generation premix, so fuel nozzle linkage section 54 subregion fuel, air equivalent are than in ignition range.When combustion chamber flame drum 38 internal combustion unstable, when tempering phenomenon occurs, can sail against the current and enter fuel nozzle linkage section 54 with the flame of the fuel nozzle linkage section 54 direct-connected combustion zones of outlet, light the fuel gas in described fuel nozzle linkage section 54, burn out calotte, even burn out the fuel nozzle assembly 32 in fuel nozzle linkage section 54.
Patent US5685139 adopts the mode of skiving nozzle end structure, even guarantee that nozzle end is burned, it still can be worked by the mode of diffusion combustion.Although this kind of scheme can guarantee that nozzle works on, can not guarantee the destruction of tempering to nozzle hardware, this effective working method is based upon the cost of pollutant emission and off-design behaviour work simultaneously.
Summary of the invention
In order to solve problems of the prior art; the purpose of this invention is to provide a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly;, when thereby flame tempering occurs the downstream combustion instability, the fuel nozzle assembly of upstream can be protected and be prevented from burning to this structure.
The technical solution adopted in the present invention is as follows:
A kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly, comprise the fuel nozzle linkage section that fuel nozzle assembly and fuel nozzle assembly are outer, and fuel nozzle assembly comprises cyclone and nozzle assembly centerbody, it is characterized in that:
Described fuel nozzle linkage section comprises the column type passage, shrinkage type passage and expanding passage.Shrinkage type passage and expanding passage junction are arranged on the downstream of nozzle assembly centerbody end axial location.
Described shrinkage type vias inner walls face and expanding vias inner walls face adopt the conical surface or cambered surface, or both combinations.
Described shrinkage type passage is greater than and flows through the area that is jammed that this fuel nozzle linkage section flow is corresponding with the throat area of expanding passage junction.
The axial length L of described shrinkage type passage
1axial length L for the expanding passage
21.3～2 times.
Be provided with one section rear column type passage after described expanding passage.
Open film cooling holes on the wall of described expanding passage; Or all open film cooling holes on described expanding channel wall He on rear column type channel wall.The tangent line angle of described film cooling holes central axis and expanding channel cross-section is between 0 °～30 °, and all central axis of film cooling holes are parallel, and aperture is between 0.1-0.5mm, and percent opening is between 35%～70%.
The present invention compared with prior art has the following advantages and the technique effect of high-lighting:
Fuel nozzle linkage section described in the combustion chamber burner linkage section assembly the present invention relates to is formed by column type passage and the shrinkage type passage be connected with the column type channel outlet and expanding combination of channels, in the well-known general knowledge of the industry, in described constricted channel, air velocity increases, in shrinkage type passage and the channel attached venturi of expanding position air velocity maximum, air-flow accelerates to prevent that tempering air-flow adverse current from entering constricted channel, effectively protected the fuel nozzle assembly of venturi upstream; Described throat area is greater than the area that is jammed, and makes gas flow rates in the shrinkage type passage be less than all the time the velocity of sound, and in described expanding passage, gas flow rates continues to reduce, the air velocity while having guaranteed steady flame burning; The axial length of described shrinkage type passage is greater than the axial length of expansion segment; with the axial length of guaranteeing the expanding passage, remain in a less scope; even the generation tempering, the tempering distance also is less than the axial length of expanding passage, effectively protects the upstream fuel nozzle assembly.
The accompanying drawing explanation
Fig. 1 is the chamber structure of prior art.
Fig. 2 is a fuel nozzle linkage segment structure sketch in prior art.
Fig. 3 is fuel nozzle linkage section the first embodiment sketch of the present invention.
Fig. 4 is fuel nozzle linkage section the second embodiment sketch of the present invention.
In figure, symbol description is as follows: the 10-gas turbine; The 12-compressor; The 14-combustion chamber; The 16-turbine; The 18-changeover portion; The 30-end-cap assembly; The 32-fuel nozzle assembly; The 33-cyclone; The water conservancy diversion lining that the 34-burner inner liner is outer; 35-propellant spray device; 36-nozzle assembly centerbody; 37-nozzle assembly centerbody end; The 38-burner inner liner; The water conservancy diversion lining that the 40-changeover portion is outer; 42-burner inner liner calotte assembly; 44-impacts Cooling Holes; 50-anti-backfire type nozzle linkage section; 54-fuel nozzle linkage section; 61-column type passage; 63-shrinkage type passage; 65-expanding passage; The 67-venturi; 68-rear column type passage; The 70-flow dead; The 71-film cooling holes
The specific embodiment
Below in conjunction with accompanying drawing, principle of the present invention, structure and the specific embodiment are described further.
Fig. 2 is a nozzle linkage section modular construction sketch in prior art.This nozzle linkage section assembly comprises fuel nozzle linkage section 54 and fuel nozzle assembly 32, and fuel nozzle assembly 32 comprises cyclone 33, propellant spray device 35 and nozzle assembly centerbody 36; Propellant spray device 35 reasonable installations are on nozzle assembly centerbody 36, and in nozzle assembly centerbody end 37 axial location upstreams; Fuel nozzle linkage section 54 comprises column type passage 61, by 62 restrictions of column type vias inner walls; When the combustion instability phenomenon occurs in fuel nozzle linkage section 54 downstreams, the flame tempering of combustion zone, enter column type passage 61, burns out the nozzle assembly centerbody 36 of its upstream, especially nozzle assembly centerbody end 37.
The first embodiment sketch that Fig. 3 is anti-backfire type nozzle linkage section assembly of the present invention.Anti-backfire type nozzle linkage section assembly 50 comprises fuel nozzle linkage section 54 and fuel nozzle assembly 32, and fuel nozzle assembly 32 comprises cyclone 33, propellant spray device 35 and nozzle assembly centerbody 36; Propellant spray device 35 reasonable installations are on nozzle assembly centerbody 36, and in nozzle assembly centerbody end 37 axial location upstreams; Described fuel nozzle linkage section 54 is to be connected in sequence by column type passage 61, shrinkage type passage 63 and expanding passage 65, and shrinkage type passage 63 and expanding passage 65 junctions 67 are arranged on the downstream of described nozzle assembly centerbody end 37 axial locations.The internal face of the internal face of described shrinkage type passage 63 and expanding passage 65 adopts the conical surface or cambered surface, or both combinations.In the present embodiment, the internal face of the internal face of shrinkage type passage and expanding passage all adopts the conical surface; The axial location of the venturi 67 that preferably, shrinkage type passage 63 is connected with expanding passage 65 is arranged on the downstream of nozzle assembly centerbody end 37 axial locations.Air-flow carries out the premix of air and fuel in whole fuel nozzle linkage section 54, during through shrinkage type passage 63, air-flow can accelerate, when tempering occurs, can prevent that the flame adverse current from entering shrinkage type passage 63, prevent from damaging the fuel nozzle assembly 32 of its upstream, especially prevent from damaging nozzle assembly centerbody end 37.
Preferably, the area of the venturi 67 that shrinkage type passage 63 is connected with expanding passage 65 is greater than the area that is jammed, make the air-flow through this cross section can not be jammed, be that flowing velocity is less than the velocity of sound, the industry is well-known, the air-flow that does not reach the velocity of sound can slow down through the expanding passage, therefore at described expanding passage 65, can not produce supersonic flow, makes this zone flow and can reach combustion stablized air velocity.Preferably, the axial length L of shrinkage type passage 63
1should be greater than the axial length L of expanding passage 65
2, the axial length L of common shrinkage type passage 63
1axial length L for expanding passage 65
21.3～2 times, with the axial length of guaranteeing expanding passage 65, remain in a less scope, even tempering occurs, the zone minimum of tempering impact.
Another preferred version of the present invention is: increased a rear column type passage 68 at expanding passage 65, guaranteed that the gas flow outlet remains unchanged with original design.Rear column type passage 68 in expanding passage 65 and downstream arranges film cooling holes 71; The industry is well-known, and may there be flow dead 70 in air-flow after the expanding passage, and while causing tempering occurs, this regional temperature is too high; Open film cooling holes 71 and can destroy flow dead and cooling to this zone.Preferably, the tangent line angle in described film cooling holes 71 central axis and expanding passage 65 cross sections is less than 30 °, and the central axis of all film cooling holes is parallel, and aperture is between 0.1～0.5mm, and percent opening is between 5%～10%.
Fig. 4 is anti-backfire type nozzle linkage section assembly the second embodiment sketch of the present invention.Anti-backfire type nozzle linkage section assembly comprises fuel nozzle linkage section 54 and fuel nozzle assembly 32, and fuel nozzle assembly 32 comprises cyclone 33, propellant spray device 35 and nozzle assembly centerbody 36; Propellant spray device 35 reasonable installations are on nozzle assembly centerbody 36, and in nozzle assembly centerbody end 37 axial location upstreams; Fuel nozzle linkage section 54 comprises column type passage 61, shrinkage type passage 63, expanding passage 65 and rear cylindrical channel 68.In the present embodiment, the internal face of described shrinkage type passage is formed by the curved surfaces of a contraction, and the internal face of described expanding passage is formed by the conical surface of an expansion.
Claims (9)
1. a gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly, this nozzle linkage section assembly comprises fuel nozzle assembly (32) and the outer fuel nozzle linkage section (54) of fuel nozzle assembly; Described fuel nozzle assembly (32) comprises cyclone (33), propellant spray device (35) and nozzle assembly centerbody (36), it is characterized in that: described fuel nozzle linkage section (54) is to be connected in sequence by column type passage (61), shrinkage type passage (63) and expanding passage (65), and shrinkage type passage (63) and expanding passage (65) junction (67) are arranged on the downstream of described nozzle assembly centerbody end (37) axial location.
2. a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly as claimed in claim 1, is characterized in that: the internal face employing conical surface or the cambered surface of the internal face of described shrinkage type passage (63) and expanding passage (65), or both combinations.
3. a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly as claimed in claim 1, it is characterized in that: described shrinkage type passage (63) is greater than and flows through the area that is jammed that this fuel nozzle linkage section (54) flow is corresponding with the throat area of expanding passage (65) junction.
4. a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly as claimed in claim 1 is characterized in that: 1.3～2 times of the axial length L 2 that the axial length L 1 of described shrinkage type passage (63) is expanding passage (65).
5. as claim 1,2,3 or 4 described a kind of gas-turbine combustion chamber anti-backfire type nozzle connecting-type channel components, it is characterized in that: be provided with rear column type passage (68) after described expansion segment (65).
6. a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly as claimed in claim 5, is characterized in that: have film cooling holes (71) on the wall of described expanding passage (65).
7. a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly as claimed in claim 6, is characterized in that: have film cooling holes (71) on the wall of described rear column type passage (68).
8. a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly as claimed in claim 6, it is characterized in that: the tangent line angle in the central axis of the film cooling holes (71) of opening on described expanding channel wall and expanding passage (65) cross section is between 0 °～30 °, all central axis of film cooling holes (71) are parallel, aperture is between 0.1～0.5mm, and percent opening is between 35%～70%.
9. a kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly as claimed in claim 7, it is characterized in that: the tangent line angle in the central axis of the film cooling holes (71) of opening on described rear column type passage (68) wall and expanding passage (65) cross section is between 0 °～30 °, all central axis of film cooling holes (71) are parallel, aperture is between 0.1～0.5mm, and percent opening is between 35%～70%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310397606.9A CN103486591B (en) | 2013-09-04 | 2013-09-04 | A kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310397606.9A CN103486591B (en) | 2013-09-04 | 2013-09-04 | A kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103486591A true CN103486591A (en) | 2014-01-01 |
| CN103486591B CN103486591B (en) | 2016-09-07 |
Family
ID=49827041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310397606.9A Active CN103486591B (en) | 2013-09-04 | 2013-09-04 | A kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103486591B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566465A (en) * | 2014-12-31 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Tempering prevention head structure |
| CN104566467A (en) * | 2014-12-31 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Anti-backfire nozzle |
| CN109596302A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flow control ejection system of dummy vehicle low-speed wind tunnel experiment |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998017951A1 (en) * | 1996-10-22 | 1998-04-30 | Siemens Westinghouse Power Corporation | MULTIPLE VENTURI ULTRA-LOW NOx COMBUSTOR |
| JP2000240910A (en) * | 1999-02-22 | 2000-09-08 | Tokyo Gas Co Ltd | Heat storage combustion type flat frame burner |
| CN101220954A (en) * | 2008-01-25 | 2008-07-16 | 上海锅炉厂有限公司 | Combustor and combustion method for pure burning blast furnace gas or low-calorific value gas |
| CN101592339A (en) * | 2008-05-28 | 2009-12-02 | 通用电气公司 | Be used for weakening fuse tube and the correlation technique that gas turbine premixed device flame keeps |
| CN102620293A (en) * | 2012-04-01 | 2012-08-01 | 北京工业大学 | Improved high-speed pressure-stabilized combustor for submerged combustion technology |
| CN203517805U (en) * | 2013-09-04 | 2014-04-02 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Backfire-preventing nozzle connecting section assembly of combustion chamber of gas turbine |
-
2013
- 2013-09-04 CN CN201310397606.9A patent/CN103486591B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998017951A1 (en) * | 1996-10-22 | 1998-04-30 | Siemens Westinghouse Power Corporation | MULTIPLE VENTURI ULTRA-LOW NOx COMBUSTOR |
| JP2000240910A (en) * | 1999-02-22 | 2000-09-08 | Tokyo Gas Co Ltd | Heat storage combustion type flat frame burner |
| CN101220954A (en) * | 2008-01-25 | 2008-07-16 | 上海锅炉厂有限公司 | Combustor and combustion method for pure burning blast furnace gas or low-calorific value gas |
| CN101592339A (en) * | 2008-05-28 | 2009-12-02 | 通用电气公司 | Be used for weakening fuse tube and the correlation technique that gas turbine premixed device flame keeps |
| CN102620293A (en) * | 2012-04-01 | 2012-08-01 | 北京工业大学 | Improved high-speed pressure-stabilized combustor for submerged combustion technology |
| CN203517805U (en) * | 2013-09-04 | 2014-04-02 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Backfire-preventing nozzle connecting section assembly of combustion chamber of gas turbine |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566465A (en) * | 2014-12-31 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Tempering prevention head structure |
| CN104566467A (en) * | 2014-12-31 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Anti-backfire nozzle |
| CN104566467B (en) * | 2014-12-31 | 2018-02-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of anti-backfire type nozzle |
| CN104566465B (en) * | 2014-12-31 | 2018-03-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of anti-backfire type head construction |
| CN109596302A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flow control ejection system of dummy vehicle low-speed wind tunnel experiment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103486591B (en) | 2016-09-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203517805U (en) | Backfire-preventing nozzle connecting section assembly of combustion chamber of gas turbine | |
| JP6262986B2 (en) | Combustion turbine engine fuel injection assembly | |
| JP6708380B2 (en) | Combustion turbine engine fuel injector assembly | |
| US2828603A (en) | Afterburner for turbo jet engines and the like | |
| US10690350B2 (en) | Combustor with axially staged fuel injection | |
| JPH09119641A (en) | Low nitrogen-oxide dilution premixing module for gas-turbineengine | |
| CN106678868A (en) | Integrated afterburner provided with deflected rectification support plate | |
| JP2015532412A (en) | Flame sheet combustor dome | |
| JP6086391B2 (en) | Annular cylindrical combustor with graded and tangential fuel-air nozzles for use in gas turbine engines | |
| CN104566471B (en) | A kind of nozzle and the gas turbine provided with the nozzle | |
| CN106958836A (en) | Bundle pipes fuel nozzle assembly with liquid fuel capacity | |
| JP5399015B2 (en) | Fuel nozzle for gas turbine engine and method of making the same | |
| RU2619673C2 (en) | Mixing of combustible substances procedure for gas turbine engine combustion chamber | |
| CN110440292B (en) | Combustor of combustion chamber of gas turbine | |
| CN108870441B (en) | Afterburner adopting circular arc fan-shaped nozzle and concave cavity structure | |
| CN110822474A (en) | Flame stabilizing structure of combustion chamber | |
| CN103822229A (en) | Low swirl nozzle for combustion chamber of gas turbine | |
| CN104315541B (en) | Combustion chamber grade nozzle on duty and the method for using the nozzle | |
| CN104613473A (en) | Multi-hole fuel gas jet flow burner | |
| CN103486591A (en) | Tempering-proof nozzle connecting section assembly of combustor of combustion gas turbine | |
| CN203731484U (en) | Low-cyclone nozzle of combustor | |
| CN102759122A (en) | Fuel nozzle and method for operating a combustor | |
| CN103822230A (en) | Low-swirl-flow nozzle of combustion chamber | |
| CN203837024U (en) | Low swirl nozzle for gas turbine combustion chamber | |
| EP3465009B1 (en) | Fuel nozzle for a gas turbine with radial swirler and axial swirler and gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: A kind of gas-turbine combustion chamber anti-backfire type nozzle linkage section assembly Effective date of registration: 20171115 Granted publication date: 20160907 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20190820 Granted publication date: 20160907 |
|
| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20191230 Granted publication date: 20160907 |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200220 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 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20160907 Pledgee: Tsinghua Holdings Co.,Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. Registration number: 2016990000853 |