CN105716113A - Double-cyclone premixing burner - Google Patents
Double-cyclone premixing burner Download PDFInfo
- Publication number
- CN105716113A CN105716113A CN201610083011.XA CN201610083011A CN105716113A CN 105716113 A CN105716113 A CN 105716113A CN 201610083011 A CN201610083011 A CN 201610083011A CN 105716113 A CN105716113 A CN 105716113A
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- Prior art keywords
- fuel nozzle
- pipe
- cyclone
- level cyclone
- bispin
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Classifications
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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
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Fuel Cell (AREA)
Abstract
Disclosed is a double-cyclone premixing burner. The double-cyclone premixing burner comprises a fuel spray nozzle, a fuel pipe, an oxidizing agent pipe, a first-level cyclone device, a second-level cyclone device and a venturi tube. The oxidizing agent pipe sleeves the fuel pipe, and the oxidizing agent pipe and the fuel pipe are arranged in a coaxial mode. A contraction pipe of the venturi tube is connected with the oxidizing agent pipe. A communicating oxidizing agent flow channel is formed between the oxidizing agent pipe and the fuel pipe and between the contraction pipe and the surface of the fuel spray nozzle, wherein the minimum cross section is arranged in a downstream outlet. The first-level cyclone device and the second-level cyclone device are arranged in the oxidizing agent flow channel in a coaxial mode, the second-level cyclone device is arranged on the outer side of the first-level cyclone device, the end of a downstream outlet of the first-level cyclone device is flush with the end of a downstream outlet of the second-level cyclone device, and the cyclone directions of the first-level cyclone device and the second-level cyclone device are opposite. The downstream portion of the contraction pipe is connected with an expansion pipe. By the adoption of the double-cyclone premixing burner, strip-shaped strong turbulent flow cutting vortexes can be generated on the downstream portion of the oxidizing agent flow channel, and are used for assisting in breaking liquid fuel and accelerating mixing of fuel and oxidizing agents, and therefore the combustion performance can be improved.
Description
Technical field
The present invention relates to aero-engine or gas turbine technology field, more particularly to a kind of bispin premix burner including injection fuel and air.
Background technology
Known burner is generally adopted single-stage cyclone technique, and the effect of eddy flow mainly forms recirculating zone and carrys out smooth combustion flame.But this single-stage vortex burner exists fuel mixes the uneven problem causing burning insufficient with oxidant.
Additionally, also has a kind of burner, its oxidant channel adopts the twin-stage cyclone technique of Intermediate Gray Venturi tube dividing plate, inward eddy is used for fuel combination and oxidant, it it is Venturi tube dividing plate outside inward eddy structure, then outside Venturi tube dividing plate and with inward eddy spacing structure one segment distance arrange contour stealth structure, contour stealth be used for supplemental oxidant in combustion atmosphere, formed second-time burning.This structure is compared single rotation burner and is improve combustibility, but the oxidant that contour stealth is out is strong to the blending effect of fuel, and Venturi tube is in high-temperature region in addition, it is easy to carbon distribution and ablated.
Summary of the invention
In view of this, it is an object of the invention to provide a kind of bispin premix burner, from principle and structure, solve the deficiency that current known technology exists.
For achieving the above object, bispin premix burner provided by the invention, it is made up of fuel nozzle, cartridge, oxidant pipe, first order cyclone, second level cyclone, Venturi tube.
Fuel nozzle is round table-like；
The major part of fuel nozzle and the cartridge seamless link of upstream, be arranged on burner centre position；
Oxidant pipe is enclosed within outside described cartridge, coaxially arranged with cartridge；
Described Venturi tube is made up of collapsible tube and expansion pipe；
Collapsible tube is enclosed within outside described fuel nozzle, coaxially arranged with fuel nozzle, and major part and upstream oxidizing dose of pipe seamless link；
Between described oxidant pipe and cartridge, the ring taper stream between annular flow path and described collapsible tube with fuel nozzle side surface constitutes an oxidant stream connected；
The minimum cross-section of described oxidant stream is arranged on lower exit position；
Coaxially arranged first order cyclone and second level cyclone in described oxidant stream；
Described second level cyclone is arranged on outside first order cyclone；
Described first order cyclone and second level cyclone lower exit end face；
Described first order cyclone and second level cyclone oppositely oriented；
Microcephaly's seamless link expansion pipe in described collapsible tube downstream.
Described bispin premix burner, wherein, fuel nozzle is gas fuel nozzle or liquid fuel nozzle.
Described bispin premix burner, wherein, the structure of liquid fuel nozzle is pressure atomization formula, pneumatic nebulization formula or fabricated structure.
Described bispin premix burner, wherein, two-stage cyclones is vane type or cellular type structure of cutting sth. askew.
Described bispin premix burner, wherein, two-stage cyclones is arranged in the annular flow path between oxidant pipe and cartridge, or in the ring taper stream between collapsible tube and fuel nozzle side surface.
Described bispin premix burner, wherein, first order cyclone swirling number is 0.6～0.8, and second level cyclone swirling number is 0.8～1.0.
Described bispin premix burner, wherein, between collapsible tube and fuel nozzle side surface, angle is 1～5 °.
Described bispin premix burner, wherein, expansion length of tube is the 0.25～0.35 of venturi throat diameter.
Described bispin premix burner, wherein, expansion pipe extension cone angle is less 3～8 ° than fuel nozzle fuel injection spray cone angle.
The first order cyclone of the present invention and second level cyclone are in the end face of lower exit, such oxidizer flow is after described two-stage cyclones structure, the vortex strip that strong turbulence is sheared is formed in downstream, and known burner is equipped with the reason of dividing plate due to the uneven gentle interposition of two-stage cyclones exit end face, find no the existence of strong turbulence shear band effect.Therefore, present invention advantage compared with prior art is as follows: the present invention passes through structure optimization and innovation, forms strong turbulence and shears vortex strip；The present invention utilizes this strong turbulence to shear vortex strip addi-tional crusher liquid fuel, accelerates the mixing of fuel and oxidant, improves combustibility；Meanwhile, present invention eliminates the Venturi tube dividing plate of two-stage cyclones middle position in known technology, eliminate combustor component carbon distribution and ablated problem.
Accompanying drawing explanation
Fig. 1 is principles of the invention structure chart；
Fig. 2 is the structural map (outline cuts 1/4) of the embodiment of the present invention 1；
Fig. 3 is the structural map (outline cuts 1/4) of the embodiment of the present invention 2；
Fig. 4 is the structural map (outline cuts 1/4) of the embodiment of the present invention 3.
Description of reference numerals in figure:
1 cartridge；2 fuel nozzles；3 oxidant pipe；4 first order cyclones；4a first order cyclone lower exit end face；5 second level cyclones；5a second level cyclone lower exit end face；6 collapsible tubes；7 expansion pipes；8 Venturi tubes；Angle between 9 collapsible tubes and fuel nozzle surface；10 fuel nozzle fuel injection spray cone angle；11 expansion pipe extension cone angles；12 oxidant streams；12a oxidant stream minimum cross-section；13 expansion length of tube；14 venturi throat diameters.
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearly understand, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in further detail.
The invention discloses a kind of bispin premix burner, its operation principle is as follows:
The lower exit end face 4a of first order cyclone 4 flushes with the lower exit end face 5a of second level cyclone 5, oxidant in annular flow path 12 in parallel through after first order cyclone 4 and second level cyclone 5, oppositely oriented due to two-stage cyclones, thus strip strong turbulence shear band can be formed in the centre position of outlet flow passage.Owing to the fuel injection angle 10 of described fuel nozzle 2 is more than the angle of flare 11 expanding pipe, so fuel can strike strong turbulence shear band in downstream, therefore fuel (if liquid fuel) can be accelerated broken, can accelerate to mix with oxidant under strong turbulence is pulsed simultaneously.Therefore this structure relies on self strong turbulence to shear aerodynamic force and enhances the mixing effect of fuel and oxidant.
More specifically, the structure of the bispin premix burner of the present invention is as it is shown in figure 1, be made up of cartridge 1, fuel nozzle 2, oxidant pipe 3, first order cyclone 4, second level cyclone 5, Venturi tube 8.Fuel nozzle 2 is round table-like；The major part of fuel nozzle 2 and cartridge 1 seamless link of upstream, be arranged on burner centre position；Oxidant pipe 3 is enclosed within outside described cartridge 1, coaxially arranged with cartridge 1；Venturi tube 8 is made up of collapsible tube 6 and expansion pipe 7；Collapsible tube 6 is enclosed within outside described fuel nozzle 2, coaxially arranged with fuel nozzle 2, and the major part of collapsible tube 6 and the seamless link of upstream oxidizing dose of pipe 3；Between annular flow path and collapsible tube 6 with fuel nozzle 2 side surface between oxidant pipe 3 with cartridge 1, ring taper stream constitutes an oxidant stream 12 connected；The minimum cross-section of oxidant stream 12 is at the cross section 12a of lower exit position；Coaxially arranged first order cyclone 4 and second level cyclone 5 in oxidant stream 12；Second level cyclone 5 is arranged on the outside of first order cyclone 4；The lower exit end face 4a and second level cyclone lower exit end face 5a of first order cyclone flush, and non-inductive windings between two-stage cyclones；First order cyclone 4 and second level cyclone 5 oppositely oriented；Microcephaly's seamless link expansion pipe 7 in collapsible tube 6 downstream.
Fuel nozzle 2 can be gas fuel nozzle or liquid fuel nozzle.Wherein, the structure of liquid fuel nozzle is pressure atomization formula, pneumatic nebulization formula or fabricated structure.The swirling number of first order cyclone 4 is between 0.6～0.8；The swirling number of second level cyclone 5 is between 0.8～1.0.Between collapsible tube 6 and fuel nozzle 2 side surface, angle 9 is 1～5 °.Expansion length of tube 13 is the 0.25～0.35 of venturi throat diameter 14, it is preferred to 0.26.Expansion pipe extension cone angle 11 is less than fuel nozzle fuel injection spray cone angle 10 3～8 °, it is preferred to 4 °.
In the present invention, first order cyclone 4 and second level cyclone 5 can be arranged in the annular flow path between oxidant pipe 3 and cartridge 1, it is also possible to be arranged in the ring taper stream between collapsible tube 6 and fuel nozzle 2 side surface；Structure can be leaf structure, it is also possible to for cellular type structure of cutting sth. askew.
Below in conjunction with drawings and Examples, technical scheme is further described.
Embodiment 1
Refer to Fig. 2, in first embodiment of the invention, have following structure:
The bispin premix burner of the present invention is made up of cartridge 1, fuel nozzle 2, oxidant pipe 3, first order cyclone 4, second level cyclone 5, Venturi tube 8, wherein: fuel nozzle 2 is round table-like；The major part of fuel nozzle 2 and cartridge 1 seamless link of upstream, be arranged on burner centre position；Oxidant pipe 3 is enclosed within outside described cartridge 1, coaxially arranged with cartridge 1；Venturi tube 8 is made up of collapsible tube 6 and expansion pipe 7；Collapsible tube 6 is enclosed within outside described fuel nozzle 2, coaxially arranged with fuel nozzle 2, and major part and the seamless link of upstream oxidizing dose of pipe 3；Between annular flow path and collapsible tube 6 with fuel nozzle 2 side surface between oxidant pipe 3 with cartridge 1, ring taper stream constitutes an oxidant stream 12 connected；The minimum cross-section of oxidant stream 12 is at the cross section 12a of lower exit position；Coaxially arranged first order cyclone 4 and second level cyclone 5 in oxidant stream 12；Second level cyclone 5 is arranged on the outside of first order cyclone 4；The lower exit end face 4a and second level cyclone lower exit end face 5a of first order cyclone flush；First order cyclone 4 and second level cyclone 5 oppositely oriented；Microcephaly's seamless link expansion pipe 7 in collapsible tube 6 downstream.
Fuel nozzle 2 can be gas fuel nozzle or liquid fuel nozzle.Wherein, the structure of liquid fuel nozzle is pressure atomization formula, pneumatic nebulization formula or fabricated structure.The swirling number of first order cyclone is 0.74；The swirling number of second level cyclone is 0.92.Between collapsible tube 6 and fuel nozzle 2 side surface, angle 9 is 2 °.Expansion length of tube 13 is the 0.26 of venturi throat diameter 14.Expansion pipe extension cone angle 11 is less than fuel nozzle fuel injection spray cone angle 10 4 °.
As in figure 2 it is shown, two-stage cyclones is arranged in the annular flow path between oxidant pipe 3 and cartridge 1 in the present embodiment, it is leaf structure.
Embodiment 2
Refer to Fig. 3, second embodiment of the invention, be structured with:
The bispin premix burner of the present invention is made up of cartridge 1, fuel nozzle 2, oxidant pipe 3, first order cyclone 4, second level cyclone 5, Venturi tube 8, wherein: fuel nozzle 2 is round table-like；The major part of fuel nozzle 2 and cartridge 1 seamless link of upstream, be arranged on burner centre position；Oxidant pipe 3 is enclosed within outside described cartridge 1, coaxially arranged with cartridge 1；Venturi tube 8 is made up of collapsible tube 6 and expansion pipe 7；Collapsible tube 6 is enclosed within outside described fuel nozzle 2, coaxially arranged with fuel nozzle 2, and major part and the seamless link of upstream oxidizing dose of pipe 3；Between annular flow path and collapsible tube 6 with fuel nozzle 2 side surface between oxidant pipe 3 with cartridge 1, ring taper stream constitutes an oxidant stream 12 connected；The minimum cross-section of oxidant stream 12 is at the cross section 12a of lower exit position；Coaxially arranged first order cyclone 4 and second level cyclone 5 in oxidant stream 12；Second level cyclone 5 is arranged on the outside of first order cyclone 4；The lower exit end face 4a and second level cyclone lower exit end face 5a of first order cyclone flush；First order cyclone 4 and second level cyclone 5 oppositely oriented；Microcephaly's seamless link expansion pipe 7 in collapsible tube 6 downstream.
Fuel nozzle 2 can be gas fuel nozzle or liquid fuel nozzle.Wherein, the structure of liquid fuel nozzle is pressure atomization formula, pneumatic nebulization formula or fabricated structure.The swirling number of first order cyclone is 0.74；Second level cyclone swirling number is 0.92.Between collapsible tube 6 and fuel nozzle 2 surface, angle 9 is 2 °.Expansion length of tube 13 is the 0.26 of venturi throat diameter 14.Expansion pipe extension cone angle 11 is less than fuel nozzle fuel injection spray cone angle 10 4 °.
As it is shown on figure 3, two-stage cyclones is arranged in the annular flow path between oxidant pipe 3 and cartridge 1 in the present embodiment, it is cellular type structure of cutting sth. askew.
Embodiment 3
Refer to Fig. 4, second embodiment of the invention, be structured with:
The bispin premix burner of the present invention is made up of cartridge 1, fuel nozzle 2, oxidant pipe 3, first order cyclone 4, second level cyclone 5, Venturi tube 8, wherein: fuel nozzle 2 is round table-like；The major part of fuel nozzle 2 and cartridge 1 seamless link of upstream, be arranged on burner centre position；Oxidant pipe 3 is enclosed within outside described cartridge 1, coaxially arranged with cartridge 1；Venturi tube 8 is made up of collapsible tube 6 and expansion pipe 7；Collapsible tube 6 is enclosed within outside described fuel nozzle 2, coaxially arranged with fuel nozzle 2, and major part and the seamless link of upstream oxidizing dose of pipe 3；Between annular flow path and described collapsible tube 6 with fuel nozzle 2 side surface between oxidant pipe 3 with cartridge 1, ring taper stream constitutes an oxidant stream 12 connected；The minimum cross-section of oxidant stream 12 is at the cross section 12a of lower exit position；Coaxially arranged first order cyclone 4 and second level cyclone 5 in oxidant stream 12；Second level cyclone 5 is arranged on the outside of first order cyclone 4；The lower exit end face 4a and second level cyclone lower exit end face 5a of first order cyclone flush；First order cyclone 4 and second level cyclone 5 oppositely oriented；Microcephaly's seamless link expansion pipe 7 in collapsible tube 6 downstream.
Fuel nozzle 2 can be gas fuel nozzle or liquid fuel nozzle.Wherein, the structure of liquid fuel nozzle is pressure atomization formula, pneumatic nebulization formula or fabricated structure.The swirling number of first order cyclone is 0.74；Second level cyclone swirling number is 0.92.Between collapsible tube 6 and fuel nozzle 2 surface, angle 9 is 2 °.Expansion length of tube 13 is the 0.26 of venturi throat diameter 14.Expansion pipe extension cone angle 11 is less than fuel nozzle fuel injection spray cone angle 10 4 °.
As shown in Figure 4, in the present embodiment, two-stage cyclones is arranged in the ring taper stream between collapsible tube 6 and fuel nozzle 2 side surface, all for cellular type structure of cutting sth. askew.
Particular embodiments described above; the purpose of the present invention, technical scheme and beneficial effect have been further described; it it should be understood that; the foregoing is only specific embodiments of the invention; it is not limited to the present invention; all within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (9)
1. a bispin premix burner, including fuel nozzle, cartridge, oxidant pipe, first order cyclone, second level cyclone and Venturi tube, it is characterised in that:
Described fuel nozzle is round table-like；
The major part of fuel nozzle and described cartridge seamless link, be arranged on the center of described bispin premix burner；
Described oxidant pipe is enclosed within outside described cartridge, coaxially arranged with described cartridge；
Described Venturi tube is made up of collapsible tube and expansion pipe；
Described collapsible tube is enclosed within outside described fuel nozzle, coaxially arranged with fuel nozzle, and described collapsible tube and described oxidant pipe seamless link；
Between described oxidant pipe and cartridge, the ring taper stream between annular flow path and described collapsible tube with fuel nozzle side surface constitutes an oxidant stream connected；
The minimum cross-section of described oxidant stream is arranged on lower exit position；
Coaxially arranged first order cyclone and second level cyclone in described oxidant stream；
Described second level cyclone is arranged on the outside of described first order cyclone；
Described first order cyclone and described second level cyclone lower exit end face；
Described first order cyclone and second level cyclone oppositely oriented；
Expansion pipe described in microcephaly's seamless link in described collapsible tube downstream.
2. bispin premix burner according to claim 1, wherein, described fuel nozzle is gas fuel nozzle or liquid fuel nozzle.
3. bispin premix burner according to claim 2, wherein, the structure of described liquid fuel nozzle is pressure atomization formula, pneumatic nebulization formula or fabricated structure.
4. bispin premix burner according to claim 1, wherein, the described first order and second level cyclone are each independently vane type or cellular type structure of cutting sth. askew.
5. bispin premix burner according to claim 1, wherein, the described first order and second level cyclone are arranged in the annular flow path between described oxidant pipe and described cartridge, or in the ring taper stream between described collapsible tube and described fuel nozzle side surface.
6. bispin premix burner according to claim 1, wherein, the swirling number of described first order cyclone is 0.6～0.8, and the swirling number of described second level cyclone is 0.8～1.0.
7. bispin premix burner according to claim 1, wherein, between described collapsible tube and described fuel nozzle side surface, angle is 1～5 °.
8. bispin premix burner according to claim 1, wherein, described expansion length of tube is the 0.25～0.35 of venturi throat diameter, it is preferred to 0.26.
9. bispin premix burner according to claim 1, wherein, described expansion pipe extension cone angle is less 3～8 ° than fuel nozzle fuel injection spray cone angle, it is preferred to 4 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610083011.XA CN105716113B (en) | 2016-02-06 | 2016-02-06 | Bispin premix burner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610083011.XA CN105716113B (en) | 2016-02-06 | 2016-02-06 | Bispin premix burner |
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| Publication Number | Publication Date |
|---|---|
| CN105716113A true CN105716113A (en) | 2016-06-29 |
| CN105716113B CN105716113B (en) | 2019-03-12 |
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| CN201610083011.XA Active CN105716113B (en) | 2016-02-06 | 2016-02-06 | Bispin premix burner |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106895397A (en) * | 2017-01-12 | 2017-06-27 | 华中科技大学 | A kind of rich or poor bimodal inner and outer ring reflux formula axle stream cyclone burner |
| CN108758693A (en) * | 2018-04-16 | 2018-11-06 | 西北工业大学 | A kind of integrated after-burner with double oil circuits and butt center wimble structure |
| CN109140438A (en) * | 2018-08-29 | 2019-01-04 | 成立航空技术有限公司 | The determination method of fuel spray cone angle in Double spiral-flow atomising device |
| CN109185878A (en) * | 2018-08-29 | 2019-01-11 | 成立航空技术有限公司 | Double spiral-flow atomising device second cyclone outlet flow method for determining dimension |
| CN109237516A (en) * | 2018-08-29 | 2019-01-18 | 成立航空技术有限公司 | The design method of the Venturi tube runner of Double spiral-flow atomising device |
| CN112999993A (en) * | 2021-02-08 | 2021-06-22 | 乌兰浩特市圣益商砼有限公司 | Vortex-spraying two-stage strengthening reactor for preparing polycarboxylate superplasticizer and preparation method |
| US11592182B1 (en) | 2021-11-16 | 2023-02-28 | General Electric Company | Swirler ferrule plate having pressure drop purge passages |
| CN117759451A (en) * | 2024-02-18 | 2024-03-26 | 北京大学 | Solid fuel continuous detonation engine based on shear mixing structure |
| CN117989564A (en) * | 2024-02-27 | 2024-05-07 | 北京航空航天大学 | Dual-fuel nozzle for low-pollution gas turbine combustor |
| US11994295B2 (en) | 2022-02-18 | 2024-05-28 | General Electric Company | Multi pressure drop swirler ferrule plate |
| US12038176B2 (en) | 2022-02-18 | 2024-07-16 | General Electric Company | Coupling a fuel nozzle purge flow directly to a swirler |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106895397B (en) * | 2017-01-12 | 2019-01-15 | 华中科技大学 | A kind of rich or poor bimodal inner and outer ring reflux formula axis stream cyclone burner |
| CN106895397A (en) * | 2017-01-12 | 2017-06-27 | 华中科技大学 | A kind of rich or poor bimodal inner and outer ring reflux formula axle stream cyclone burner |
| CN108758693A (en) * | 2018-04-16 | 2018-11-06 | 西北工业大学 | A kind of integrated after-burner with double oil circuits and butt center wimble structure |
| CN109140438B (en) * | 2018-08-29 | 2020-07-21 | 成立航空技术有限公司 | Method for determining fuel spray cone angle in double-cyclone atomization device |
| CN109185878A (en) * | 2018-08-29 | 2019-01-11 | 成立航空技术有限公司 | Double spiral-flow atomising device second cyclone outlet flow method for determining dimension |
| CN109237516A (en) * | 2018-08-29 | 2019-01-18 | 成立航空技术有限公司 | The design method of the Venturi tube runner of Double spiral-flow atomising device |
| CN109140438A (en) * | 2018-08-29 | 2019-01-04 | 成立航空技术有限公司 | The determination method of fuel spray cone angle in Double spiral-flow atomising device |
| CN112999993A (en) * | 2021-02-08 | 2021-06-22 | 乌兰浩特市圣益商砼有限公司 | Vortex-spraying two-stage strengthening reactor for preparing polycarboxylate superplasticizer and preparation method |
| CN112999993B (en) * | 2021-02-08 | 2023-04-07 | 乌兰浩特市圣益商砼有限公司 | Vortex-spraying two-stage strengthening reactor for preparing polycarboxylate superplasticizer and preparation method |
| US11592182B1 (en) | 2021-11-16 | 2023-02-28 | General Electric Company | Swirler ferrule plate having pressure drop purge passages |
| US11994295B2 (en) | 2022-02-18 | 2024-05-28 | General Electric Company | Multi pressure drop swirler ferrule plate |
| US12038176B2 (en) | 2022-02-18 | 2024-07-16 | General Electric Company | Coupling a fuel nozzle purge flow directly to a swirler |
| CN117759451A (en) * | 2024-02-18 | 2024-03-26 | 北京大学 | Solid fuel continuous detonation engine based on shear mixing structure |
| CN117759451B (en) * | 2024-02-18 | 2024-04-26 | 北京大学 | Solid fuel continuous detonation engine based on shear mixing structure |
| CN117989564A (en) * | 2024-02-27 | 2024-05-07 | 北京航空航天大学 | Dual-fuel nozzle for low-pollution gas turbine combustor |
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Effective date of registration: 20210913 Address after: 251401 room A107, Cuizhai business center, No. 1, central street, Cuizhai street, Jiyang District, Jinan City, Shandong Province Patentee after: Jinan Zhongke Xianxian Gas Turbine Technology Co.,Ltd. Address before: 100190, No. 11 West Fourth Ring Road, Beijing, Haidian District Patentee before: Institute of Engineering Thermophysics, Chinese Academy of Sciences |