CN104791828B - Flame stabilization device of supersonic speed combustion chamber - Google Patents
Flame stabilization device of supersonic speed combustion chamber Download PDFInfo
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- CN104791828B CN104791828B CN201510226302.5A CN201510226302A CN104791828B CN 104791828 B CN104791828 B CN 104791828B CN 201510226302 A CN201510226302 A CN 201510226302A CN 104791828 B CN104791828 B CN 104791828B
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- oxidizing agent
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Abstract
The invention discloses a flame stabilization device of a supersonic speed combustion chamber. The flame stabilization device comprises a supporting plate, oxidizing agent through holes, spiral guiding grooves and fuel guiding tubes. The supporting plate is fixedly installed inside the supersonic speed combustion chamber, the oxidizing agent through holes are formed inside the supporting plate and used for conveying oxidizing agents, the spiral guiding grooves are formed in the inner walls of the oxidizing agent through holes and used for driving the oxidizing agents to spirally rotate inside the oxidizing agent through holes, and the fuel guiding tubes are arranged inside the oxidizing agent through holes and used for conveying fuel. Through forming the oxidizing agent through holes with the spiral guiding grooves inside the supporting plate, the oxidizing agents will be output clockwise and anticlockwise in a spiral rotation mode when passing through the oxidizing agent through holes; meanwhile, because the fuel guiding tubes are arranged inside the oxidizing agent through holes, the fuel will be driven by the oxidizing agents to rotate when output at an outlet, then mixing of the fuel and the oxidizing agents is effectively improved, and the combustion efficiency of the fuel is improved; in addition, by the adoption of the structure, the pressure loss at the mixing position of the fuel and the oxidizing agents is small, and flame stability can be effectively guaranteed.
Description
Technical field
The present invention relates to supersonic combustor, more specifically, more particularly to a kind of supersonic combustor flame stabilization dress
Put.
Background technology
There is the mixing that the premise of burning is that fuel and oxidant reach molecular level in fuel, and in some high-velocity combustion dresses
Put, such as in supersonic combustor, air velocity is very fast, air-flow is very short in the indoor residence time of burning, so as to fuel and
Oxidant is often difficult to be sufficiently mixed, and so significantly impacts the efficiency of combustion of fuel.
In order to improve the efficiency of combustion of fuel, scholars are carried out to fuel in supersonic combustor with the mixing of oxidant
Substantial amounts of research.Research shows in supersonic combustor fuel and oxidant mixed layer, there is substantial amounts of large scale eddy,
When these whirlpool Accelerating runnings, little vortex shock wave will be formed.Little vortex shock wave can reduce the scale of turbulence and produce reversely vortex,
Significantly impact fuel in turbulent flow to mix with oxidant.Therefore, it is the mixing of enhancing fuel and oxidant, generally requires to adopt it
Its mode produces vortex, and oxidant is involved in into The fuel stream core, increases the contact area of fuel and oxidant so that molecule spreads
Can more fully carry out.
At present enhancing fuel mixes with oxidant typically two ways：Active and passive type.Active mixing strengthens
Method mainly using the external disturbance of active control to excite shear layer in unstable wave produce vortex, strengthen shear layer and mix
Close.Such as disturbance is introduced using oscillating plate/line, the sound wave for producing certain frequency using pulsing jet enters row energization to shear layer, but
It is that realizing for active mixing enhancement techniques is more complicated, but also need in addition install control device additional, and this can be to supersonic combustion
Additional weight load is brought in room, significantly impacts normally using for supersonic combustor.Passive mixing Enhancement Method is current
A kind of method for commonly using, it is usually to strengthen fuel using special geometry to mix with oxidant.
Accompanying drawing 1 provides a kind of existing supersonic combustor flame stabilizer, and the device is by after support plate 01
Edge arranges interlaced lobe type structure 02, and so guiding air mixes to flow with fuel.Although this existing structure can
To improve the mixing of fuel and oxidant to a certain extent, but during using this structure, the flow direction that the trailing edge of support plate 01 is produced
Whirlpool and shock wave can bring obvious pitot loss, so significantly impact the stability of flame.
In sum, how a kind of mixing that can strengthen fuel and oxidant is provided, the efficiency of combustion of fuel is improved, and
Can guarantee that the supersonic combustor flame stabilizer of flame holding becomes those skilled in the art's problem demanding prompt solution.
The content of the invention
The technical problem to be solved in the present invention is a kind of supersonic combustor flame stabilizer of offer, the supersonic combustion
Room flame stabilizer can strengthen the mixing of fuel and oxidant by its structure design, improve the efficiency of combustion of fuel, and
Can guarantee that flame holding.
A kind of supersonic combustor flame stabilizer, including：
Support plate, is mounted on the supersonic combustion chamber interior；
Oxidant through hole, is arranged at described intralaminar part, for the transmission of oxidant；
Helical guide groove, is arranged at the oxidant through-hole wall, for driving oxidant to revolve in oxidant through hole internal coiling
Turn；
Fuel conductor, is arranged inside the oxidant through hole, for the transmission of fuel.
Preferably, the support plate is wedge shape support plate.
For further oxidation reinforced dose with the mixing of fuel, it is preferable that the oxidant through hole is same with the fuel conductor
The center of circle is arranged.
Preferably, reverse acting spiral guide groove is provided with the fuel conductor, the reverse acting spiral guide groove is used to drive fuel
In fuel conductor internal coiling rotation, and make fuel direction of rotation contrary with oxidant direction of rotation.
Preferably, at least 2 oxidant through holes are provided with the support plate.
Preferably, the oxidant through hole is not less than 1.25 with the internal diameter ratio of the fuel conductor.
The invention has the beneficial effects as follows：The supersonic combustor flame stabilizer is led by arranging band spiral in support plate
The oxidant through hole of groove, meeting is counterclockwise or clock wise spirals rotation is exported when passing through oxidant through hole so as to oxidant, while by
It is arranged on inside oxidant through hole in fuel conductor, therefore, fuel can be oxidized agent when exit exports and be rotated, so as to
Effectively strengthen the mixing of fuel and oxidant, improve the efficiency of combustion of fuel；Additionally, using fuel during this structure and oxidant
The pressure loss at mixing is less, and flame holding can be effectively ensured.
Description of the drawings
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description is briefly described, it should be apparent that, drawings in the following description are only this
Inventive embodiment, for those of ordinary skill in the art, on the premise of not paying creative work, can be with basis
The accompanying drawing of offer obtains other accompanying drawings.
Fig. 1 is a kind of flame stabilizer structural representation of prior art；
Fig. 2 is the supersonic combustor flame stabilizer overall structure diagram of embodiment 1；
Fig. 3 is the supersonic combustor flame stabilizer right view of embodiment 1；
Fig. 4 is the supersonic combustor flame stabilizer top view of embodiment 1；
Fig. 5 is the supersonic combustor flame stabilizer left view of embodiment 1；
Fig. 6 is the supersonic combustor flame stabilizer front view of embodiment 1；
Fig. 7 is the supersonic combustor flame stabilizer B-B direction sectional view of embodiment 1；
Fig. 8 is the structural representation of embodiment 2.
Specific embodiment
In order that those skilled in the art more fully understand the technical scheme in the application, below in conjunction with the application reality
The accompanying drawing in example is applied, the technical scheme in the embodiment of the present application is clearly and completely described, it is clear that described enforcement
Example is only some embodiments of the present application, rather than the embodiment of whole.
Based on the embodiment in the application, those of ordinary skill in the art are obtained under the premise of creative work is not made
The every other embodiment for obtaining, should all belong to the scope of the application protection.
Embodiment 1：
As shown in accompanying drawing 2 to accompanying drawing 7, accompanying drawing 2 to accompanying drawing 7 provides a kind of tool of supersonic combustor flame stabilizer
Body embodiment.
The supersonic combustor flame stabilizer includes：Support plate 1, is mounted on supersonic combustion chamber interior.
Oxidant through hole 2, is arranged inside support plate 1, for the transmission of oxidant, for the quantity of oxidant through hole 2, and can
With specifically chosen as needed, 3 parallel oxidant through holes 2 are provided with the present embodiment.The one end of oxidant through hole 2 is
Air inlet, for the input of oxidant；One end is gas outlet, for the output of oxidant, wherein, the oxidant of the present embodiment leads to
The air inlet of hole 2 is arranged on the leading edge of support plate 1, and gas outlet is arranged on the trailing edge of support plate 1.
Helical guide groove 3, is arranged at the inwall of oxidant through hole 2, for driving oxidant to revolve in the internal coiling of oxidant through hole 2
Turn, specifically, when helical guide groove 3 is to arrange clockwise, oxidant turns clockwise in oxidant through hole 2, when spiral is led
When groove 3 is to arrange counterclockwise, oxidant rotate counterclockwise in oxidant through hole 2.For the concrete structure of helical guide groove 3, also
Other modes can be adopted, as long as it can drive oxidant spiral rotating.
Fuel conductor 4, is arranged inside oxidant through hole 2, for the transmission of fuel.Fuel conductor 4 includes fuel inlet
And fuel outlet, the turnover of fuel is respectively used to, in the present embodiment, fuel inlet is arranged at the side of support plate 1, and fuel outlet is arranged
In the trailing edge of support plate 1, thus, mixing when at oxidant and fuel transmission to the trailing edge of support plate 1.
When being embodied as, input oxidant, such as incoming air in oxidant through hole 2, incoming air is in helical guide groove 3
In the presence of can be rotating current transmission in the internal coiling of oxidant through hole 2, when air is exported at the gas outlet of oxidant through hole 2
When, can mix with the fuel exported from the fuel port of fuel conductor 4, because now air rotates in high speed, therefore, air meeting
Drive fuel to rotate together, so as to effectively enhance the mixing of fuel and air, improve the efficiency of combustion of fuel；Additionally, using
Fuel and air will not be stopped mixing place by other structures during this structure, therefore its pressure loss is less, can be effective
Ensure flame holding.
In the present embodiment, support plate 1 is preferably wedge shape support plate.Thus, it is relatively simple for structure, use and process all relatively more square
Just.Certainly, in practical operation, it is also possible to using the support plate 1 of other structures form, as long as it can meet design requirement i.e.
Can.
It is the mixing of further oxidation reinforced dose and fuel in the present embodiment, oxidant through hole 2 is with fuel conductor 4 with circle
The heart is arranged.Thus, when fuel is exported from the fuel outlet of fuel conductor 4, the turning moment suffered by fuel surrounding is of substantially equal, such as
This, can further oxidation reinforced dose with the mixing of fuel, the oxidant and fuel mixture ratio for preventing zones of different differ too big.
In the present embodiment, reverse acting spiral guide groove 5 is provided with fuel conductor 4, reverse acting spiral guide groove 5 is used to drive fuel to exist
The internal coiling of the fuel conductor 4 rotates, and makes fuel direction of rotation with oxidant direction of rotation conversely, thus, fuel and oxidation
Agent can interlock in the trailing edge exit of support plate 1, can so be more conducive to the mixing of oxidant and fuel.
Abundant burning in view of fuel at least needs to ensure that oxidant has certain mixing ratio, oxidant through hole with fuel
2 are not less than 1.25 with the internal diameter ratio of fuel conductor 4.In the present embodiment, the internal diameter of fuel conductor 4 be 1mm, the internal diameter of oxidant through hole 2
For 1.25mm, oxidant through hole 2 is arranged with the concentric of fuel conductor 4.
Generally, the supersonic combustor flame stabilizer that the present invention is provided does not increase extra injection device,
Directly reach enhancing mixed effect come stream using supersonic oxidizing dose of air-flow.The program is using along counterclockwise or ejection clockwise
The oxidizer flow for coming drives fuel rotation, strengthens the mixed effect of fuel and oxidant, improves efficiency of combustion.Additionally, oxidation
Agent is less with the pressure loss at fuel mixing, and flame holding can be effectively ensured.
Embodiment 2：
Present invention also offers specific embodiment when a kind of supersonic combustor flame stabilizer is used, wherein, Fig. 8
Structural representation when using in runner is arranged on for apparatus of the present invention.
As shown in Figure 8, the runner that the present embodiment is provided highly is 50mm, and runner leading portion top and bottom are parallel, apart from support plate
Runner upper surface expands outwardly 3 ° at leading edge 23mm, and support plate 1 is arranged on the centre position of the runner short transverse, and the present embodiment makes
Support plate 1 is wedge shape support plate, wedge shape support plate overall length 32mm, and the distance of wedge shape support plate leading edge to fuel conductor 4 is 23mm, wedge
Shape support plate upper surface and lower surface angle are 12 °.
When being embodied as, the input air in oxidant through hole 2, air velocity Ma=2.Wherein, Ma represents Mach number, Ma
=v/c, is the ratio of speed v with the local velocity of sound c of the point of certain point in flow field, i.e. Ma is the number for representing velocity of sound multiple, in physics
Mach number is commonly referred to as on, is a dimensionless number, one Mach is one times of velocity of sound, and two Mach is two times of velocities of sound.That is this enforcement
The air velocity of input is two times of velocities of sound in oxidant through hole 2 in example.
In the present embodiment, while inputting hydrogen is used as fuel, hydrogen flow rate Ma=1, i.e. hydrogen flow rate in fuel conductor 4
For one times of velocity of sound.The oxidant obtained in being embodied as is as shown in table 1 with the contrast of fuel mixed effect：
Wherein, table 1 the 1st is classified as measurement distance, and the present embodiment measures the Data Comparison of 5 points altogether, respectively distance
Plate trailing edge distance is 0.01m, 0.02m, 0.03m, 0.04m, 0.05m, and the 2nd is classified as using oxidant during conventional apparatus and fuel
Mixing efficiency, the 3rd is classified as the mixing efficiency using oxidant during apparatus of the present invention and fuel.
Table 1
By table 1：
The use of conventional apparatus mixing efficiency is 0.053456, using the present invention when being 0.01m apart from support plate trailing edge distance
Device mixing efficiency is 0.323552；
The use of conventional apparatus mixing efficiency is 0.059342, using the present invention when being 0.02m apart from support plate trailing edge distance
Device mixing efficiency is 0.306254；
The use of conventional apparatus mixing efficiency is 0.076458, using the present invention when being 0.03m apart from support plate trailing edge distance
Device mixing efficiency is 0.294953；
The use of conventional apparatus mixing efficiency is 0.12458, using the present invention when being 0.04m apart from support plate trailing edge distance
Device mixing efficiency is 0.278473；
The use of conventional apparatus mixing efficiency is 0.212533, using the present invention when being 0.05m apart from support plate trailing edge distance
Device mixing efficiency is 0.285114.
Can clearly be found out by above-mentioned data analysiss, after the device using the present invention, oxidant is imitated with the mixing of fuel
Rate is greatly improved.
A kind of supersonic combustor flame stabilizer provided by the present invention is described in detail above.Herein
Apply specific case to be set forth the principle and embodiment of the present invention, the explanation of above example is only intended to help
Understand the method for the present invention and its core concept.It should be pointed out that for those skilled in the art, do not taking off
On the premise of the principle of the invention, some improvement and modification can also be carried out to the present invention, these are improved and modification also falls into this
In invention scope of the claims.
Claims (6)
1. a kind of supersonic combustor flame stabilizer, including：
Support plate, is mounted on the supersonic combustion chamber interior；
Oxidant through hole, is arranged at described intralaminar part, for the transmission of oxidant；Characterized in that,
Helical guide groove, is arranged at the oxidant through-hole wall, for driving oxidant to rotate in oxidant through hole internal coiling；
Fuel conductor, is arranged inside the oxidant through hole, for the transmission of fuel.
2. supersonic combustor flame stabilizer according to claim 1, it is characterised in that the support plate is wedge shape
Plate.
3. supersonic combustor flame stabilizer according to claim 1, it is characterised in that the oxidant through hole with
The fuel conductor concentric is arranged.
4. supersonic combustor flame stabilizer according to claim 1, it is characterised in that set in the fuel conductor
Reverse acting spiral guide groove is equipped with, the reverse acting spiral guide groove is used to drive fuel to rotate in the fuel conductor internal coiling, and makes combustion
Material direction of rotation is contrary with oxidant direction of rotation.
5. supersonic combustor flame stabilizer according to claim 1, it is characterised in that be provided with the support plate
At least 2 oxidant through holes.
6. supersonic combustor flame stabilizer according to claim 1, it is characterised in that the oxidant through hole with
The internal diameter ratio of the fuel conductor is not less than 1.25.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510226302.5A CN104791828B (en) | 2015-05-06 | 2015-05-06 | Flame stabilization device of supersonic speed combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510226302.5A CN104791828B (en) | 2015-05-06 | 2015-05-06 | Flame stabilization device of supersonic speed combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104791828A CN104791828A (en) | 2015-07-22 |
| CN104791828B true CN104791828B (en) | 2017-05-03 |
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ID=53556855
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510226302.5A Active CN104791828B (en) | 2015-05-06 | 2015-05-06 | Flame stabilization device of supersonic speed combustion chamber |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112728584B (en) * | 2020-11-24 | 2021-12-07 | 南京航空航天大学 | Flame stabilizer, radial flame stabilizer and combustion chamber |
| CN113123898B (en) * | 2021-04-19 | 2022-06-07 | 中国人民解放军国防科技大学 | Supersonic flow mixing device based on jet flow disturbance at rear edge of partition plate |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4903480A (en) * | 1988-09-16 | 1990-02-27 | General Electric Company | Hypersonic scramjet engine fuel injector |
| JP2953160B2 (en) * | 1991-12-27 | 1999-09-27 | 日産自動車株式会社 | Scrumjet engine |
| US5660040A (en) * | 1994-12-20 | 1997-08-26 | United Technologies Corporation | Scramjet fuel injection system having independent fuel supplies for supersonic and hypersonic operation |
| JPH08219408A (en) * | 1995-02-08 | 1996-08-30 | Ishikawajima Harima Heavy Ind Co Ltd | Combustor for supersonic speed |
| FR2745605B1 (en) * | 1996-03-01 | 1998-04-30 | Aerospatiale | FUEL INJECTION DEVICE FOR AIRCRAFT STATOREACTOR |
| CN101435586A (en) * | 2007-11-15 | 2009-05-20 | 周建兴 | Supersonic speed combustion chamber scheme of step / groove composite injection structure |
| EP2230455B1 (en) * | 2009-03-16 | 2012-04-18 | Alstom Technology Ltd | Burner for a gas turbine and method for locally cooling a hot gases flow passing through a burner |
| CN202303431U (en) * | 2011-10-22 | 2012-07-04 | 云南思创格科技有限责任公司 | Screw type safe mixing device for water gas and air |
| CN102980206B (en) * | 2012-12-18 | 2014-12-24 | 中国人民解放军国防科学技术大学 | Flame stabilizer and engine combustion chamber comprising same |
| CN104019464B (en) * | 2014-05-28 | 2016-02-17 | 中国人民解放军国防科学技术大学 | The method for designing of engine, flameholder and cavity thereof |
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