CN109442479A - A kind of compound thermal protection structure and rotation detonation engine of combustion chamber wall surface - Google Patents
A kind of compound thermal protection structure and rotation detonation engine of combustion chamber wall surface Download PDFInfo
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- CN109442479A CN109442479A CN201811092426.9A CN201811092426A CN109442479A CN 109442479 A CN109442479 A CN 109442479A CN 201811092426 A CN201811092426 A CN 201811092426A CN 109442479 A CN109442479 A CN 109442479A
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- combustion chamber
- resistance
- protection
- ablation
- thermal protection
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M5/00—Casings; Linings; Walls
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M5/00—Casings; Linings; Walls
- F23M5/08—Cooling thereof; Tube walls
-
- 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
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
Abstract
The present invention provides a kind of compound thermal protection structure of combustion chamber wall surface, includes passive thermal protection and active thermal protection, and passive thermal protection includes thermal insulation layer and the flexible layer of resistance to ablation protection；It axially flows the cooling duct that active thermal protection is distributed in the flexible layer of resistance to ablation protection by entering fuel oil through combustion chamber, combustion chamber participation burning is again introduced into after absorbing heat by heat convection, fuel oil heat absorption is utilized to be cooled down, it can help fuel oil heating again to be conducive to igniting starting, tissue burning, improve efficiency of combustion.Passive thermally protective materials are run through at the inclined angle of divergence hole, can not only help micro-molecular gas of the material of the flexible layer of resistance to ablation protection after by thermal cracking to overflow, but also can prevent combustion gas from flowing backward, reaching the adherent effect of Film Cooling.The present invention can improve the thermal protective performance of combustion chamber, improve the reliability of combustion chamber, facilitate the service life for increasing combustion chamber.Present invention simultaneously provides the rotation detonation engines with the compound thermal protection structure.
Description
Technical field
The invention belongs to the designs of aero-engine cooling structure and thermal protection technology field.
The present invention still belongs to the technical field of aero-engine structure design.
Background technique
Rotation detonation engine (Rotating Detonation Engine, RDE) is a kind of based on detonating combustion mechanism
New engine, generally use annular-shaped combustor open at one end closed at one end, propellant is sprayed from the closed end of combustion chamber
Enter, combustion product is discharged from the other end.High-speed rotating detonation wave is generated when work, from the circumferentially rotatable biography of head of combustion chamber
It broadcasts, as the high speed discharge of combustion product generates thrust.Compared to conventional engines, have structure is simple, development cost is low,
The advantages that big specific impulse, high thrust ratio, has good development prospect, is increasingly becoming international and national and researches and develops new and effective boat
The hot spot of empty airspace engine.
When detonation wave carries out high speed rotation propagation in annular firing room, speed is in 1200~2500m/s, burning vibration
Swing frequency up to tens of thousands of hertz, burning room temperature is more up to 1500~2500 DEG C, and state-of-the-art high temperature resistant composite wood at present
The maximum heat resisting temperature for expecting C-C and SiC is 2200K.As the continuous high speed of detonation wave rotates, pinking product and chamber wall
Strong heat exchange can occur between face, steeply rise wall surface temperature, wall heat flux density is up to 0.6MW/m2.Due to lacking
Few effective cooling protection, rotation detonation engine working time are often shorter.It is existing studies have shown that thermal protection technology
The key factor of rotation detonation engine development is restricted through becoming.Therefore, carry out grinding for rotation detonation engine thermal protection scheme
Study carefully one of the work for needing to carry out at present.
Combustion chamber is maximum along axial middle section and back segment mean heat flux, is the significant points for implementing thermal protection.It is existing
Thermal protection technology be mainly passive thermal protection, the protective layer constructed such as temperature resistant rubber and SiC.But with rotation pinking hair
The extension of motivation working time, passive protection thickness degree needs are significantly increased, this is undoubtedly to combustion chamber volume and engine weight
It affects, also not can guarantee the implementation result of thermal protection.Active thermal protection carries out chamber structure by cryogen cold
But, but coolant flow is limited, and cooling capacity is also limited.
Summary of the invention
Goal of the invention: disclosed by the invention is a kind of compound thermal protection structure led and passively combined, to improve combustion chamber
The heat shock resistance time of wall surface, its cooling potential is sufficiently excavated under the premise of not increasing thermal protection shield thickness, utilization is limited
Carrier of the fuel as re-generatively cooled, the cooling efficiency for improving fuel can greatly improve the service life of protective layer, extend
The safe operation time of detonation engine.
Present invention simultaneously provides a kind of detonation engines containing compound thermal protection structure.
Technical solution: in order to achieve the above objectives, following skill can be used in the compound thermal protection structure of combustion chamber wall surface of the present invention
Art scheme:
A kind of compound thermal protection structure of combustion chamber wall surface, which implements inside outer wall of combustion chamber, according to by extroversion
Interior sequence is sequentially arranged the flexible layer of resistance to ablation protection, thermal insulation layer and high emissivity coating；Edge inside the flexible layer of resistance to ablation protection
Combustion chamber axially arrangement circulation passage；Multiple divergence holes are arranged on thermal insulation layer；The divergence hole extends internally through high emission
Rate coating is simultaneously connected to combustion chamber；The cross section of combustion chamber is circle, and divergence hole extending direction is with respect to the circular radius
Linear angle at an acute angle.
The high frequency of wall surface is washed away the utility model has the advantages that on the one hand combustion chamber wall surface will bear detonation wave high-temperature fuel gas, another party
Face will bear the intense radiation heating of luminous flame, and therefore, heat flow density suffered by this region wall surface is high, and has unsteady
Pulse characteristic.Requirement far can not be reached by temperature-resistant material merely to carry out thermal protection.In order to solve this problem,
Active cooling compound cooling structure is regenerated using passive thermal protection+fuel oil, is realized by ablation resistance of material and heat insulation
Protection to engine metal wall surface first flows into before injecting combustion chamber by low temperature kerosene and is distributed in Inner Wall of Combustion Chamber flexibility
The regeneration flow channel arranged in the layer of resistance to ablation protection, cools down high-temperature wall surface.High emissivity coating can pass through
Height radiation reduces the heat for reaching the flexible thermal layer of resistance to ablation protection by thermal insulation layer, and it is anti-that this partial heat enters flexible resistance to ablation
It is taken away after sheath by ablation resistant material and low temperature kerosene.Wherein ablation resistant material can be by melting, gas after reaching certain temperature
The modes such as change are slowly cracked into micro-molecular gas, these gases take away heat by the discrete aperture discharge on thermal insulation layer, and lead to
It crosses inclination aperture and forms air film in compound wall surface, can also further stop high-temperature fuel gas.Low temperature kerosene passes through fuel pump
Suction its unidirectional operation in circulation passage may be implemented, reach it is optimal continue cooling effect.This operation has double
Recast is used, and the low temperature kerosene that on the one hand can be effectively absorbs heat by heat convection, when extending the use of ablation resistant material
Between, own temperature increases after another aspect low temperature kerosene absorbs heat, is conducive to it and enters indoor full combustion of burning.
In conclusion the advantages of invention is: composite protection structure is simple, it is easy to accomplish combustion chamber wall surface temperature ladder
Spend small, wall surface temperature is low；Aviation kerosine repeats unidirectional outflow, and heat convection rate is high；The gas that ablation resistant material overflows returns to combustion
Burn the heat-insulated air film of indoor formation；Temperature increases more conducively tissue burning after aviation kerosine executes supercooling task.
Further, further include on the outer wall of combustion chamber and with the nozzle opening that is directly connected in combustion chamber；The nozzle opening
Outside be connected to circulation passage by oil pipe.
It further, further include the fuel tank being equally connected to circulation passage, the engine fuel in fuel tank is from circulation passage
It is sprayed into combustion chamber after into oil pipe from nozzle opening.
Further, high emissivity coating emissivity is 0.8~0.95.
Further, the flexible layer of resistance to ablation protection is after thermal insulation layer absorption heat, and a part of heat is by low temperature kerosene through square
Shape circulation passage is taken away, and another part heat passes through the micro-molecular gas that the flexible layer of resistance to ablation protection cracks generation at high temperature
It takes away, this portion gas is overflowed by divergence hole through thermal insulation layer and emissivity coating.
Further, diverging bore dia is between 0.5~1.0mm, and divergence hole extending direction is with respect to the circular radius
The angle for forming acute angle is 20 °~40 °, and divergence hole axial alignment spacing and circumferential array spacing ratio are 1.5~3.5.
Further, the flexible layer of resistance to ablation protection the selection of material be the silicon rubber of resistance to ablation, multidirectional braiding C-C composite,
One of silicon based composite material；The material of thermal insulation layer is organosilicon and ceramic material；The cross sectional shape of circulation passage is pros
One or more of shape, rectangle, circle；The ratio of passage flow cross-sectional width and temperature resistant rubber cross-sectional width is 0.5~
2。
Following technical solution can be used in detonation engine provided by the invention:
A kind of rotation detonation engine, including combustion chamber, the cross section of the combustion chamber is annular, and combustion chamber has circle
The inner wall of cylindrical outer wall and cylinder；Combustion chamber is formed between outer wall and inner wall；Outer wall is equipped with and combustion chamber
The nozzle opening being directly connected to；It is characterized in that, compound thermal protection structure is arranged on the inside of the Inner Wall of Combustion Chamber；The compound thermal is anti-
Protection structure is sequentially arranged the flexible layer of resistance to ablation protection, thermal insulation layer and high emissivity coating according to the sequence of ecto-entad；It is flexible resistance to
Ablation protection layer is posted by outer wall inner surface；Circulation passage is axially arranged along combustion chamber inside the flexible layer of resistance to ablation protection；?
Multiple divergence holes are arranged on thermal insulation layer；The divergence hole extends internally through high emissivity coating and is connected to combustion chamber；
The fuel tank and oil pipe being connected to circulation passage are additionally provided on outer wall, the outside of nozzle opening is logical by oil pipe and circulation
Road connection；Engine fuel in fuel tank sprays into combustion chamber after entering oil pipe from circulation passage from nozzle opening.
Further, high emissivity coating emissivity is 0.8~0.95.The flexible layer of resistance to ablation protection is absorbed from thermal insulation layer
After heat, a part of heat is taken away by low temperature kerosene through rectangle circulation passage, and another part heat passes through flexible resistance to ablation protection
The micro-molecular gas that layer cracks generation at high temperature is taken away, this portion gas is by divergence hole through thermal insulation layer and emissivity coating
It overflows.
Rotation detonation engine provided by the invention uses passive thermal protection+fuel oil and regenerates active cooling Compound cooling
Structure is realized the protection to engine metal wall surface by ablation resistance of material and heat insulation, is being infused by low temperature kerosene
The regeneration flow channel for being distributed in and arranging in the flexible layer of resistance to ablation protection of Inner Wall of Combustion Chamber is first flowed into before entering combustion chamber, to high temperature
Wall surface cools down.It is anti-that high emissivity coating can reach the resistance to ablation of flexible thermal by thermal insulation layer by height radiation reduction
The heat of sheath, this partial heat are taken away after entering the flexible layer of resistance to ablation protection by ablation resistant material and low temperature kerosene.Wherein
Ablation resistant material, which reaches after certain temperature, to be slowly cracked into micro-molecular gas by the modes such as melt, gasify, these gases are logical
Heat is taken away in the discrete aperture discharge crossed on thermal insulation layer, and forms air film in compound wall surface by inclination aperture, can also be into
One step stops high-temperature fuel gas.Its unidirectional operation in circulation passage may be implemented by the suction of fuel pump in low temperature kerosene, reaches
Continue cooling effect to optimal.This operation has double action, and the low temperature kerosene that on the one hand can be passes through heat convection
Heat is effectively absorbed, the time that uses of ablation resistant material is extended, another aspect low temperature kerosene absorbs own temperature liter after heat
Height is conducive to it and enters indoor full combustion of burning.
Detailed description of the invention
Fig. 1 is the structural schematic diagram for rotating detonation combustor；
Fig. 2 is the diagrammatic cross-section of Fig. 1；
Fig. 3 is fuel oil re-generatively cooled structural schematic diagram；
Fig. 4 is the arrangement schematic diagram of divergence hole；
Specific embodiment
With reference to the accompanying drawings and examples, the principle of the present invention, structure and specific embodiment work are further retouched in detail
It states.
Embodiment one
The present embodiment provides a kind of compound thermal protection structures of combustion chamber wall surface.
Fig. 1 is the structural schematic diagram of typical rotation detonation combustor, including toroidal combustion chamber 4, outer wall of combustion chamber 2, combustion
Burn chamber interior walls 3.Gaseous fuel enters through import 1, mixes with the fuel oil by fuel feed hole 5, generates detonation wave, pinking through igniting
Wave along axial high speed rotate propagate when, speed in 1200~2500m/s, combustion chamber 4 temperature at 1500 DEG C~2500 DEG C
Between, much higher than the normal working temperature of combustion chamber wall surface, it is therefore desirable to implement effective thermal protection.The present invention is compound thermal
Protection method organically combines low temperature fuel oil re-generatively cooled+passive thermal protection.Air is sucked through import 1, is sprayed into nozzle opening 5
Fuel oil mixing after in the combustion chamber tissue burning, generate rotation detonation wave along toroidal combustion chamber axially movable, through jet pipe 7
Discharge.
Fig. 2 show A-A cross section view of the invention, and Fig. 3 is fuel oil re-generatively cooled structural schematic diagram, and Fig. 4 is divergence hole
Arrangement schematic diagram.
Meet in thermal protection structure design at this, is sequentially arranged the flexible layer of resistance to ablation protection according to the sequence of ecto-entad
12, thermal insulation layer 9 and high emissivity coating 8.The flexible layer of resistance to ablation protection 12 is posted by 2 inner surface of outer wall.Flexible resistance to ablation protection
Circulation passage 11 is axially arranged along combustion chamber inside layer 12.11 width of channel and rubber are~2 than 0.5 at width.Divergence hole
10 run through heat-barrier material 9 with 20 °~40 ° inclinations angle.
It along the structure of combustion chamber wall surface is from outside to inside constructed by passive thermal protection and active thermal protection in overall structure
Composite construction.Active thermal guard section is undertaken by fuel oil, from fuel tank 13 come out after along circulation passage 11 flow, by right
Flow the cooling flexible layer of resistance to ablation protection 12 of heat exchange mode；Nozzle opening 5 is flowed back into from oil pipe 14 after fuel oil absorption heat, is realized
Recycling；The flexible layer of resistance to ablation protection 12 absorbs heat from thermal insulation layer 9, and a part of heat is taken away by fuel oil, itself is heated
After reach one surely temperature gradually melt, gasify, this portion gas will along divergence hole 10 tilt flow out.Divergence hole 10 is oblique
Hole (cross section of combustion chamber is circle, and divergence hole extending direction forms the angle of acute angle with respect to the circular radius), diverging
The angle α of hole and circular radius is 20 °~40 °, for comparing straight hole, and spilling gas can on the one hand flowed in hole
Path is elongated, increases air flowing time, is conducive to heat convection；On the other hand, tiltedly go out stream can prevent combustion gas reverse irrigation and
And it can achieve the adherent effect of better air film；Thermal insulation layer 9 becomes the first of protection combustion chamber wall surface by its lower thermal conductivity
The strong barrier in road, high emissivity coating 8 thereon further reduce the heat by thermal insulation layer 9.
Fig. 4 is the arrangement schematic diagram of divergence hole, and rhomboid distribution, axial alignment spacing and circumferential array is presented in divergence hole
Spacing ratio is 1.5~3.5；Divergence hole hole inner section shape be circle, aperture between 0.5~1.0mm, hole inclination angle be 20 °~
40°。
Embodiment two
The present embodiment provides a kind of rotation detonation engines.
The rotation detonation engine, including the combustion chamber 4 in such as Fig. 1,2.The cross section of the combustion chamber 4 is annular, and is fired
Burn the inner wall 2 that room has cylindrical outer wall 3 and cylinder.Combustion chamber is formed between outer wall 3 and inner wall 2.On outer wall 3
Equipped with the nozzle opening 5 being directly connected to combustion chamber.
The rotation detonation engine has the compound thermal protection structure such as embodiment one kind.Meanwhile it being additionally provided on outer wall 3
The fuel tank 13 and oil pipe 14 being connected to circulation passage.The outside of nozzle opening 5 is connected to by oil pipe 14 with circulation passage 11.Fuel tank
Engine fuel in 13 sprays into combustion chamber from after the entrance oil pipe 14 of circulation passage 11 from nozzle opening 5.High emissivity coating hair
Penetrating rate is 0.8~0.95.The flexible layer of resistance to ablation protection is after thermal insulation layer absorption heat, and a part of heat is by low temperature kerosene through square
Shape circulation passage is taken away, and another part heat passes through the micro-molecular gas that the flexible layer of resistance to ablation protection cracks generation at high temperature
It takes away, this portion gas is overflowed by divergence hole through thermal insulation layer and emissivity coating.
The present invention implement the technical solution method and approach it is very much, the above is only preferred reality of the invention
Apply mode.It should be pointed out that for those skilled in the art, without departing from the principle of the present invention,
Several improvement can also be made, these improvement also should be regarded as protection scope of the present invention.Each composition being not known in the present embodiment
The available prior art in part is realized.
Claims (10)
1. a kind of compound thermal protection structure of combustion chamber wall surface, which is characterized in that the structure is implemented in outer wall of combustion chamber (2)
Portion is sequentially arranged the flexible layer of resistance to ablation protection (12), thermal insulation layer (9) and high emissivity coating (8) according to the sequence of ecto-entad；
The flexible layer of resistance to ablation protection (12) is internal axially to arrange circulation passage (11) along combustion chamber；It is arranged on thermal insulation layer (9) multiple
Divergence hole (10)；The divergence hole extends internally through high emissivity coating (8) and is connected to combustion chamber；
The cross section of combustion chamber is circle, and divergence hole (10) extending direction forms the angle of acute angle with respect to the circular radius.
2. the compound thermal protection structure of combustion chamber wall surface according to claim 1, it is characterised in that: further include being located at burning
On chamber outer wall and with the nozzle opening (5) that is directly connected in combustion chamber；The outside of the nozzle opening (5) is logical by oil pipe (14) and circulation
Road (11) connection.
3. the compound thermal protection structure of combustion chamber wall surface according to claim 2, it is characterised in that: further include equally with stream
The fuel tank of circulation passage (11) connection, engine fuel in fuel tank from nozzle opening spray into combustion chamber after entering oil pipe from circulation passage
It is interior.
4. the compound thermal protection structure of combustion chamber wall surface according to claim 1 or 2 or 3, it is characterised in that: high emissivity
Coating (8) emissivity is 0.8~0.95.
5. the compound thermal protection structure of combustion chamber wall surface according to claim 1 or 2 or 3, it is characterised in that: flexible resistance to burning
Protective layer (12) are lost after thermal insulation layer (9) absorption heat, a part of heat is taken away by low temperature kerosene through rectangle circulation passage (11),
Another part heat passes through the micro-molecular gas that the flexible layer of resistance to ablation protection (12) cracks generation at high temperature and takes away, this part gas
Body is overflowed by divergence hole (10) through thermal insulation layer (9) and emissivity coating (8).
6. the compound thermal protection structure of combustion chamber wall surface according to claim 5, it is characterised in that: divergence hole (10) diameter
Between 0.5~1.0mm, divergence hole (10) extending direction with respect to the angle that the circular radius forms acute angle be 20 °~
40 °, divergence hole (10) axial alignment spacing and circumferential array spacing ratio are 1.5~3.5.
7. the compound thermal protection structure of combustion chamber wall surface according to claim 6, it is characterised in that: flexible resistance to ablation protection
Layer (12) the selection of material is one of the silicon rubber of resistance to ablation, multidirectional braiding C-C composite, silicon based composite material；Thermal insulation layer
(9) material is organosilicon and ceramic material；The cross sectional shape of circulation passage (11) is square, one in rectangle, circle
Kind is several；The ratio of passage flow cross-sectional width and temperature resistant rubber cross-sectional width is 0.5~2.
8. a kind of rotation detonation engine, including combustion chamber, the cross section of the combustion chamber is annular, and combustion chamber has cylinder
Outer wall and cylinder inner wall；Combustion chamber is formed between outer wall and inner wall；Outer wall is equipped with direct with combustion chamber
The nozzle opening (5) of connection；It is characterized in that, compound thermal protection structure is arranged on the inside of the Inner Wall of Combustion Chamber；The compound thermal protection
Structure is sequentially arranged the flexible layer of resistance to ablation protection (12), thermal insulation layer (9) and high emissivity coating according to the sequence of ecto-entad
(8)；The flexible layer of resistance to ablation protection (12) is posted by outer wall inner surface；The flexible layer of resistance to ablation protection (12) is internal along combustion chamber axis
To arrangement circulation passage (11)；Multiple divergence holes (10) are arranged on thermal insulation layer (9)；The divergence hole extends internally through high emission
Rate coating (8) is simultaneously connected to combustion chamber；
The fuel tank being connected to circulation passage (11) and oil pipe (14) are additionally provided on outer wall, nozzle opening passes through oil pipe on the outside of (5)
(14) it is connected to circulation passage (11)；Engine fuel in fuel tank, which sprays into after entering oil pipe from circulation passage from nozzle opening, to burn
It is indoor.
9. rotation detonation engine according to claim 8, it is characterised in that: high emissivity coating (8) emissivity is 0.8
~0.95.
10. rotation detonation engine according to claim 8 or claim 9, it is characterised in that: the flexible layer of resistance to ablation protection (12) from
After thermal insulation layer (9) absorbs heat, a part of heat is taken away by low temperature kerosene through rectangle circulation passage (11), and another part heat is logical
It crosses the flexible layer of resistance to ablation protection (12) and cracks the micro-molecular gas of generation at high temperature and take away, this portion gas passes through divergence hole
(10) it is overflowed through thermal insulation layer (9) and emissivity coating (8).
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| CN201811092426.9A CN109442479B (en) | 2018-09-19 | 2018-09-19 | A kind of compound thermal protection structure and rotation detonation engine of combustion chamber wall surface |
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| CN112761793A (en) * | 2021-02-03 | 2021-05-07 | 中南大学 | Wall surface heat insulation/explosion-proof integrated thermal protection structure of combustion chamber of rotary detonation engine |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110469871A (en) * | 2019-09-09 | 2019-11-19 | 西北工业大学 | A kind of Compound cooling rotation detonation combustor based on Stirling cycle |
| CN110566999A (en) * | 2019-09-20 | 2019-12-13 | 清华大学 | Combustion chamber thermal protection wall surface structure utilizing fuel oil self-suction sweating cooling |
| CN110566999B (en) * | 2019-09-20 | 2020-07-28 | 清华大学 | Combustion chamber thermal protection wall surface structure utilizing fuel oil self-suction sweating cooling |
| CN112761793A (en) * | 2021-02-03 | 2021-05-07 | 中南大学 | Wall surface heat insulation/explosion-proof integrated thermal protection structure of combustion chamber of rotary detonation engine |
| CN113464283A (en) * | 2021-08-10 | 2021-10-01 | 南京航空航天大学 | Compound initiative cooling structure of rotatory detonation engine and rotatory detonation engine |
| CN113464283B (en) * | 2021-08-10 | 2022-10-21 | 南京航空航天大学 | Compound initiative cooling structure of rotatory detonation engine and rotatory detonation engine |
| CN114233516A (en) * | 2021-12-23 | 2022-03-25 | 南京航空航天大学 | Composite material detonation engine combustion chamber structure with regenerative cooling function |
| CN114294679A (en) * | 2022-01-06 | 2022-04-08 | 中南大学 | Compound thermal protection concave cavity combustion chamber |
| CN116557169A (en) * | 2023-07-10 | 2023-08-08 | 中国人民解放军空军工程大学 | Device and method for regulating and controlling working mode of rotary detonation engine by using plasma |
| CN116557169B (en) * | 2023-07-10 | 2023-09-19 | 中国人民解放军空军工程大学 | Device and method for regulating and controlling working mode of rotary detonation engine by using plasma |
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