CN109113895B - Flame stabilizing device of ramjet engine - Google Patents
Flame stabilizing device of ramjet engine Download PDFInfo
- Publication number
- CN109113895B CN109113895B CN201811054052.1A CN201811054052A CN109113895B CN 109113895 B CN109113895 B CN 109113895B CN 201811054052 A CN201811054052 A CN 201811054052A CN 109113895 B CN109113895 B CN 109113895B
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- Prior art keywords
- air
- flame
- flame stabilization
- cyclone
- fuel nozzle
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
-
- 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The utility model provides a ramjet flame stabilising arrangement, includes centrifugal fuel nozzle, straight-flow fuel nozzle, flame stabilization base and air swirler, flame stabilization base is whole to be the annular, has arranged a plurality of air swirler in flame stabilization base's inner space, between the air swirler and between air swirler and the flame stabilization base be connected fixedly through the carriage, centrifugal fuel nozzle is the same with air swirler's quantity and corresponds the setting respectively on an air swirler, straight-flow fuel nozzle is the same with air swirler's quantity, straight-flow fuel nozzle sets up on flame stabilization base and in flame stabilization base's the circumferencial direction on with air swirler position crisscross setting each other. The invention forms local rotational flow at the head of the combustion chamber of the ramjet engine, the central vortex of the rotational flow can effectively stabilize flame, and rotational flow gas ignites downstream mixed air. The flame stabilizer has the advantages of small flow resistance, wide flame stabilizing range and easy thermal protection.
Description
Technical field
The invention belongs to field of aerospace technology, and in particular to a kind of punching engine that flame-stabilizing area is generated using eddy flow
Flame stabilizer.
Background technique
Publication No. 105546578A, publication date are a kind of application for a patent for invention --- flame stabilization on May 4th, 2016
Device is to overcome the problems, such as that the oil-gas ratio in flameholder recirculating zone is difficult to control, on the basis of annular V type groove, increases
Radial V-groove, and multiple suction holes have been opened on it, recirculating zone entered with pumps fuel.
Publication No. 106642202A, publication date be on May 10th, 2017 application for a patent for invention --- one kind is used for
The flame stabilizer of the Asia TBCC burning ramjet combustion chamber, with an improved traditional supporting plate schemes, by increasing on supporting plate
Cavity, while the spray fuel oil in the air chamber in cavity forward position enhance the atomization and evaporation of fuel oil, can be in wider wide scope
Realize flame stabilization.
But above-mentioned flame stabilizer has the shortcomings that flow resistance is big, thermal protection is difficult.Typical V-groove or branch
The blockage ratio of plate needs to can be only achieved enough pressure differences 40% or more, and rear along low speed recirculating zone is formed, so big is stifled
Plug ratio just increases flow resistance；Simultaneously as flame burns in V-groove bottom or supporting plate side, flame temperature is high, hot-fluid
Greatly, thermal protection is highly difficult, for example, Publication No. 106642202A, publication date is the patent of invention Shen on May 10th, 2017
Please --- a kind of flame in the flame stabilizer for the Asia the TBCC burning ramjet combustion chamber just cavity on supporting plate
It is interior, it is difficult to solar heat protection.
Summary of the invention
In view of the defects existing in the prior art, the present invention provides a kind of punching engine flame stabilizer.
To realize the above-mentioned technical purpose, the technical scheme is that
A kind of punching engine flame stabilizer, including centrifuging temperature nozzle, single flow fuel nozzle, flame stabilization
Pedestal and air cyclone, the flame stabilization pedestal is whole in a ring, arranges in the inner space of flame stabilization pedestal
There are multiple air cyclones, passes through support frame between air cyclone and between air cyclone and flame stabilization pedestal and connect
Fixed, centrifuging temperature nozzle is identical as the quantity of air cyclone and respectively corresponds setting on an air cyclone, direct current
Formula fuel nozzle is identical as the quantity of air cyclone, and the setting of single flow fuel nozzle is on flame stabilization pedestal and steady in flame
Determine on the circumferential direction of pedestal with air cyclone position to be interlaced setting.
In the present invention, flame stabilization pedestal is circular ring shape, all air cyclones circular distribution axisymmetricly and all
The central axis of annulus where air cyclone is overlapped with the central axis of flame stabilization pedestal.Further, institute of the present invention
The diameter D for stating flame stabilization pedestal is determined by following relational expression:
Wherein,It is respectively air mass flow and density with ρ, is engine population parameter；U is air velocity, general to choose
Air velocity is 40~80m/s, preferably 60m/s.
The present invention is disposed with multiple air cyclones, the number of air cyclone in the inner space of flame stabilization pedestal
Usually 3~6, when the diameter D of flame stabilization pedestal is smaller, 3 are chosen, when the diameter D of flame stabilization pedestal is larger,
Choose 6.Air cyclone is chosen for axial-flow type, and air cyclone is made of inner cylinder, outer cylinder and swirl vane；Inner cylinder setting exists
Outer barrel, inner barrel and outer barrel are that cylinder-shaped and the two is coaxially disposed, the central axis and flame stabilization base of inner barrel and outer barrel
The centerline axis parallel of seat.Multi-disc swirl vane uniformly and be circumferentially laid on inner tank theca, swirl vane be prismatic blade or
Bent blade usually chooses 8~16.Incoming air is flowed into from the side of air cyclone, which is swirl vane entrance, is come
The side that stream air is flowed out through air cyclone is swirl vane outlet.Swirl vane entrance and inside/outside cylinder axis direction are flat
Row, it is angle of impeller outlet alpha that swirl vane outlet, which is formed by angle with axis direction, and general angle of impeller outlet alpha is 30~60 degree
Angle, preferably 45 degree.The eddy flow degree S of air cyclone is generally chosen for 0.6~1.0, preferably 0.8, here, air cyclone
Eddy flow degree be measure air rotation important parameter, is defined as:
Wherein, α is outlet blade angle, and Z is the ratio between swirl vane internal diameter and outer diameter, usually 0.3~0.7, preferably
0.5；Swirl vane is with a thickness of 1~2mm.
Air cyclone is processed using essence casting or 3D printing integration.Between adjacent air cyclone and air swirl
Connected by support frame between device and flame stabilization pedestal, support frame thickness in 10mm between 20mm, fire can be transmitted
Flame, and flow resistance can be reduced.
In the present invention, each centrifuging temperature nozzle is separately positioned on inside its inner cylinder of each air cyclone.Specifically, it is centrifuged
The mode that formula fuel nozzle is connected through a screw thread or welds is connected to inside its inner cylinder of air cyclone.When swirl vane rotates
The centrifuging temperature nozzle rotation being able to drive in inner cylinder and inner cylinder.Its spout of centrifuging temperature nozzle is towards incoming air through sky
The side of cyclonic current device outflow.Incoming air is flowed into from the side of air cyclone, after air cyclone, generates rotation
Air forms velocity air whirlpool inside the rotary air；Meanwhile the centrifugal atomizing fuel oil sprayed through centrifuging temperature nozzle will
It is well mixed with incoming air, forms low speed combustion mixture.
In the present invention, each single flow fuel nozzle is evenly distributed on flame stabilization pedestal, on flame stabilization pedestal
The distance between adjacent single flow fuel nozzle is equal.Corresponding position on flame stabilization pedestal offers each single flow fuel oil
The mounting hole of nozzle, the mode that each single flow fuel nozzle is connected through a screw thread or welds be connected on flame stabilization pedestal and
Each its spout of single flow fuel nozzle is towards the inner space of flame stabilization pedestal.Incoming air is from the side of flame stabilization pedestal
Flow into, from single flow fuel nozzle spray fuel oil radial penetration air while be atomized on one side, diameter when track is by spraying
To the transverse direction in the same direction with incoming air is switched to, lateral atomized fuel is formed.
The centrifuging temperature nozzle and single flow fuel nozzle and its design method are well known in the art, referring to text
Offer " nozzle technology handbook " (Hou Lingyun, Sinopec publishing house, 2007).
Compared with prior art, the present invention can generate following technical effect:
The present invention utilizes and improves the eddy flow ejector filler in aero-engine, is formed on scramjet combustor head
Local eddy flow, the middle vortex cordis of the eddy flow can effectively stable flame, eddy flow combustion gas refires the mixing air of fair current.Its tool of the present invention
Have the advantages that flow resistance is small, steady flame range is wide, thermal protection is easy.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention.
Fig. 2 is cross-sectional view of the invention.
In figure:
1, flame stabilization pedestal；2, air cyclone；3, centrifuging temperature nozzle；4, single flow fuel nozzle；5, it supports
Frame；6, air cyclone outer cylinder；7, air cyclone inner cylinder；8, swirl vane；9, incoming air；10, centrifugal atomizing fuel oil；
11, velocity air whirlpool；12, lateral atomized fuel.
Specific embodiment
With reference to the accompanying drawing, embodiments of the present invention are described in further detail.
Referring to Figures 1 and 2, the present invention provides a kind of punching engine flame stabilizer, including centrifuging temperature nozzle
3, single flow fuel nozzle 4, flame stabilization pedestal 1 and air cyclone 2.
Flame stabilization pedestal 1 is axial symmetry body of revolution structure.Flame stabilization pedestal 1 is circular ring shape, in flame stabilization pedestal 1
Inner circular space in be disposed with multiple air cyclones 2,3 skies are arranged in the present embodiment in flame stabilization pedestal 1
Cyclonic current device 2.All air cyclones 2 are evenly distributed on the same annulus and the central axis of the annulus and flame stabilization base
The central axis of seat 1 is overlapped.
The selection of the diameter D of the present embodiment Flame stabilizing base 1 predominantly guarantees that air velocity is 60m/s.Flame is steady
The length L for determining pedestal 1 is 0.8 times of diameter D.
Air cyclone is axial-flow type, is made of air cyclone inner cylinder 7, air cyclone outer cylinder 6 and swirl vane 8；
Air cyclone inner cylinder 7 is arranged inside air cyclone outer cylinder 6, and air cyclone inner cylinder 7 and air cyclone outer cylinder 6 are
Cylinder-shaped and the two is coaxially disposed, the central axis and flame stabilization pedestal of air cyclone inner cylinder 7 and air cyclone outer cylinder 6
1 centerline axis parallel.
The bent blade of the use of swirl vane 8 in the present embodiment, totally 12.Swirl vane 8 is uniform and is circumferentially laid in air
On 7 outer wall of cyclone inner cylinder.Swirl vane entrance is parallel with axis direction, and at 45 degree, swirl vane is thick for outlet and axis direction
Degree is 2mm.Air cyclone 2 is processed using 3D printing integration, is connected between each air cyclone by support frame 5, air
Cyclone 2 is connect with flame stabilization pedestal 1 also by support frame 5, support frame 5 with a thickness of 15mm.
Centrifuging temperature nozzle 3 is placed in inside its inner cylinder of air cyclone 2, the mode and air swirl being connected through a screw thread
Its inner cylinder of device 2 is coaxially connected, and swirl vane 8 is able to drive the centrifuging temperature nozzle 3 in inner cylinder and inner cylinder and rotates when rotating.
Single flow fuel nozzle 4 totally 3,3 single flow fuel nozzles 4 are uniformly distributed around flame stabilization pedestal 1.The spray of single flow fuel oil
Mouth 4 is arranged on flame stabilization pedestal 1 and is mutually to hand in the circumferential position of flame stabilization pedestal 1 and 2 position of air cyclone
Mistake setting.Corresponding position on flame stabilization pedestal 1 offers the mounting hole of each single flow fuel nozzle 4, each single flow
The mode that fuel nozzle 4 is connected through a screw thread or welds be connected on flame stabilization pedestal 1 and each single flow fuel nozzle 4 its
Spout is towards the inner space of flame stabilization pedestal 1.
Fig. 2 is cross-sectional view of the invention.Incoming air 9 is flowed into from the side of air cyclone 2, by air cyclone 2
Afterwards, the air for generating rotation forms velocity air whirlpool 11 inside the rotary air；Meanwhile the rotation of swirl vane 8 drives inner cylinder
And the centrifuging temperature nozzle 3 in inner cylinder rotates.The centrifugal atomizing fuel oil 10 sprayed through centrifuging temperature nozzle 3 will be with incoming flow
Air well mixes, and forms low speed combustion mixture.Under conditions of different incoming air 9, the size in velocity air whirlpool and strong
Degree is different, but all has the characteristics that speed is low, mixes, and has good flame stabilization ability.In addition, from flame stabilizing base is located at
The fuel oil that the direct current fuel nozzle 4 of 1 side sprays, pressure difference is typically larger than 0.5MPa, under the pressure difference, fuel oil one side radial penetration
Air is atomized on one side, and radial direction when track is by spraying switchs to the transverse direction in the same direction with incoming air, forms lateral atomized fuel 12,
The transverse direction atomized fuel 12 will be by the flame ignition after air cyclone 2.Either centrifugal atomizing fuel oil 10, or laterally
Atomized fuel 12, burning all have left the flame stabilizer (punching engine flame stabilizer), also with chamber wall
There is certain distance in face, and this reduces the difficulty of thermal protection.
Technical effect of the invention is mainly manifested in following aspect:
(1) present invention can be formed stable by the combination using air cyclone and centrifuging temperature nozzle in downstream
Low speed whirlpool, and fuel-oil atmozation is good, mixes with air uniformly, realizes wide scope and stablizes flame.
(2) blocked area of air cyclone of the present invention is less than 25%, to reduce flow resistance.
(3) flame etc. after the flame, single flow fuel nozzle in air cyclone downstream of the invention is to burn from wall,
To which the temperature of near wall is low, thermal protection is easy.
The foregoing is merely a preferred embodiment of the present invention, are not intended to restrict the invention, for this field
For technical staff, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of punching engine flame stabilizer, it is characterised in that: sprayed including centrifuging temperature nozzle, single flow fuel oil
Mouth, flame stabilization pedestal and air cyclone, the flame stabilization pedestal is whole in a ring, in the inside of flame stabilization pedestal
It is disposed with multiple air cyclones in space, passes through between air cyclone and between air cyclone and flame stabilization pedestal
Support frame is connected and fixed, and centrifuging temperature nozzle is identical as the quantity of air cyclone and respectively corresponds setting in an air swirl
On device, single flow fuel nozzle is identical as the quantity of air cyclone, and single flow fuel nozzle is arranged on flame stabilization pedestal
It and on the circumferential direction of flame stabilization pedestal is interlaced setting with air cyclone position.
2. punching engine flame stabilizer according to claim 1, it is characterised in that: flame stabilization pedestal is annulus
Shape, the central axis and flame of the annulus where all air cyclones circular distribution axisymmetricly and all air cyclones
The central axis of stabilizing base is overlapped.
3. punching engine flame stabilizer according to claim 2, it is characterised in that: the flame stabilization pedestal
Diameter D is determined by following relational expression:
Wherein,It is respectively air mass flow and density with ρ；U is air velocity.
4. punching engine flame stabilizer according to claim 2, it is characterised in that: the number of air cyclone is
3~6.
5. punching engine flame stabilizer according to claim 1,2,3 or 4, it is characterised in that: air cyclone
It is chosen for axial-flow type, air cyclone is made of inner cylinder, outer cylinder and swirl vane；Inner cylinder setting is in outer barrel, inner cylinder and outer
Cylinder is that cylinder-shaped and the two is coaxially disposed, the central axis of inner barrel and outer barrel and the centerline axis parallel of flame stabilization pedestal；
Multi-disc swirl vane is uniform and is circumferentially laid on inner tank theca, and swirl vane is prismatic blade or bent blade；Incoming flow is empty
Gas is flowed into from the side of air cyclone, which is swirl vane entrance, the side that incoming air is flowed out through air cyclone
As swirl vane exports；
Swirl vane entrance is parallel with inner cylinder axis direction, and it is that blade goes out that swirl vane outlet, which is formed by angle with axis direction,
Bicker α, angle of impeller outlet alpha are 30~60 degree of angles.
6. punching engine flame stabilizer according to claim 5, it is characterised in that: the eddy flow degree of air cyclone
S is chosen for 0.6~1.0；The eddy flow degree of air cyclone is the important parameter for measuring air rotation, is defined as:
Wherein, α is outlet blade angle；Z is the ratio between swirl vane internal diameter and outer diameter, and value is 0.3~0.7.
7. punching engine flame stabilizer according to claim 1,2,3 or 4, it is characterised in that: air cyclone
It is processed using essence casting or 3D printing integration；Between adjacent air cyclone and air cyclone and flame stabilization pedestal it
Between by support frame connect, support frame thickness is in 10mm between 20mm.
8. punching engine flame stabilizer according to claim 1,2,3 or 4, it is characterised in that: centrifuging temperature
The mode that nozzle is connected through a screw thread or welds is connected to inside its inner cylinder of air cyclone；Swirl vane being capable of band when rotating
Centrifuging temperature nozzle rotation in dynamic inner cylinder and inner cylinder；Its spout of centrifuging temperature nozzle is towards incoming air through air swirl
The side of device outflow；Incoming air is flowed into from the side of air cyclone, after air cyclone, generates the air of rotation,
Velocity air whirlpool is formed inside the rotary air；Meanwhile the centrifugal atomizing fuel oil sprayed through centrifuging temperature nozzle will with come
Stream air well mixes, and forms low speed combustion mixture.
9. punching engine flame stabilizer according to claim 8, it is characterised in that: each single flow fuel nozzle is equal
Even to be distributed on flame stabilization pedestal, the distance between the adjacent single flow fuel nozzle on flame stabilization pedestal is equal.
10. punching engine flame stabilizer according to claim 9, it is characterised in that: on flame stabilization pedestal
Corresponding position offer the mounting hole of each single flow fuel nozzle, each single flow fuel nozzle is connected through a screw thread or welds
Mode be connected on flame stabilization pedestal and each its spout of single flow fuel nozzle is towards the inner space of flame stabilization pedestal；
Incoming air from the side of flame stabilization pedestal flow into, from single flow fuel nozzle spray fuel oil radial penetration air while
Atomization, radial direction when track is by spraying switch to the transverse direction in the same direction with incoming air, form lateral atomized fuel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811054052.1A CN109113895B (en) | 2018-09-11 | 2018-09-11 | Flame stabilizing device of ramjet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811054052.1A CN109113895B (en) | 2018-09-11 | 2018-09-11 | Flame stabilizing device of ramjet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109113895A CN109113895A (en) | 2019-01-01 |
| CN109113895B true CN109113895B (en) | 2019-08-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811054052.1A Active CN109113895B (en) | 2018-09-11 | 2018-09-11 | Flame stabilizing device of ramjet engine |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111780160B (en) * | 2020-08-21 | 2022-03-08 | 中国科学院工程热物理研究所 | Blunt body flame stabilizer with whirl stationary vortex structure |
| CN114165356B (en) * | 2021-11-25 | 2023-01-10 | 北京动力机械研究所 | Miniature ramjet engine |
| CN114440259B (en) * | 2021-12-14 | 2023-01-17 | 西安航天动力研究所 | Spliced flame stabilizing device with multiple oil supply paths |
| CN115234944B (en) * | 2022-07-14 | 2024-06-21 | 中国人民解放军国防科技大学 | Ramjet combustion chamber with swirl combined flame stabilization |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB766310A (en) * | 1953-05-12 | 1957-01-16 | United Aircraft Corp | Improvements in or relating to ramjet power plants |
| JP3785656B2 (en) * | 1995-09-14 | 2006-06-14 | 石川島播磨重工業株式会社 | Ram combustor |
| EP0924470B1 (en) * | 1997-12-19 | 2003-06-18 | MTU Aero Engines GmbH | Premix combustor for a gas turbine |
| US20090199563A1 (en) * | 2008-02-07 | 2009-08-13 | Hamilton Sundstrand Corporation | Scalable pyrospin combustor |
| CN107036089B (en) * | 2017-04-19 | 2019-02-01 | 中国科学院工程热物理研究所 | A kind of nozzle and burner of multiple dimensioned swirling flow atomizing |
| CN107143880B (en) * | 2017-05-16 | 2020-02-14 | 西北工业大学 | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine |
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2018
- 2018-09-11 CN CN201811054052.1A patent/CN109113895B/en active Active
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