CN113700574A - A reinforcing mixing device for solid rocket ramjet - Google Patents
A reinforcing mixing device for solid rocket ramjet Download PDFInfo
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- CN113700574A CN113700574A CN202111104516.7A CN202111104516A CN113700574A CN 113700574 A CN113700574 A CN 113700574A CN 202111104516 A CN202111104516 A CN 202111104516A CN 113700574 A CN113700574 A CN 113700574A
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- plate
- flow dividing
- splitter
- solid rocket
- rocket ramjet
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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
- F02K7/18—Composite ram-jet/rocket engines
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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
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
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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
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention provides an enhanced mixing device for a solid rocket ramjet, which comprises an air inlet channel, wherein a lobe mixer is arranged in the air inlet channel, the lobe mixer comprises a flow dividing bent plate and a lobe body, and the flow dividing bent plate is fixed on the inner wall of the air inlet channel; the lobe body comprises at least one first flow dividing plate, a curved plate and a second flow dividing plate, and the first flow dividing plate and the second flow dividing plate are connected through the curved plate; the top edges of the first flow dividing plate, the curved plate and the second flow dividing plate are sequentially fixed on the flow dividing bent plate, and the bottom edges are sequentially connected and then are in a rectangular corrugated shape; the included angle of the projection of the plate surfaces of the first splitter plate and the second splitter plate is an included angle.
Description
Technical Field
The invention relates to the technical field of solid rocket ramjet engines, in particular to an enhanced mixing device for a solid rocket ramjet engine.
Background
The solid rocket ramjet combines the solid rocket engine and the ramjet, takes oxygen in the air as an oxidant, mixes and burns with primary fuel-rich gas generated by the gas generator in the afterburning chamber and converts the fuel-rich gas into kinetic energy through the jet pipe, so that the specific impulse of the engine can be obviously improved by 3-5 times compared with the solid rocket engine. Compared with a liquid rocket ramjet engine, the hydraulic rocket ramjet engine has the advantages of simple structure, low cost, short combat response time, good maneuverability and safety and the like, and has good application prospect.
At present, the high-energy boron-containing rich-combustion propellant is one of the most energy rich-combustion propellants and is also the most ideal propulsion energy source for the solid rocket ramjet. However, the melting point and the ignition point of boron are much higher than those of aluminum and magnesium, so that the secondary combustion structure of boron particles in the afterburner chamber of the solid rocket ramjet engine is more difficult. In order to improve the combustion efficiency, the boron-containing rich fuel gas and the air need to be mixed efficiently in a low resistance in the afterburning chamber. The scheme of improving the combustion efficiency is to increase the pressure in the afterburning chamber, improve the air-fuel ratio and adjust the air inlet angle and the distance of an air inlet passage, which directly changes the structural size of the original engine and does not meet the actual requirements of engineering.
Disclosure of Invention
In view of the above-mentioned shortcomings in the prior art, the present invention provides an enhanced blending device for a solid rocket ramjet engine, which aims to enhance the combustion efficiency in a combustion chamber without changing the structural size of the original engine.
In order to achieve the purpose, the invention adopts the following technical scheme:
an enhanced mixing device for a solid rocket ramjet is provided, the solid rocket ramjet comprises an air inlet channel, a lobe mixer is arranged in the air inlet channel,
the lobe blender comprises a flow dividing bent plate and a lobe body, wherein the flow dividing bent plate is fixed on the inner wall of the air inlet channel;
the lobe body comprises at least one first flow dividing plate, a curved plate and a second flow dividing plate, and the first flow dividing plate and the second flow dividing plate are connected at intervals through the curved plate; the top edges of the first flow dividing plate, the curved plate and the second flow dividing plate are sequentially fixed on the flow dividing bent plate, and the bottom edges are sequentially connected and then are in a rectangular corrugated shape; the projection of the plate surfaces of the first splitter plate and the second splitter plate forms an included angle.
The principle of this scheme reinforcing mixing device does: the bottom edges of the first flow dividing plate, the second flow dividing plate and the curved plate are connected in sequence and then are in a rectangular corrugated shape, and the air generates spanwise vortexes caused by Kelvin-Helmholtz instability at the rectangular corrugated position of the lobe blender and induces flow direction vortexes.
The invention has the beneficial effects that: compared with the background, the formed spanwise vortex and the flow direction vortex enhance the turbulence and the vorticity of the gas and the air, enhance the mixing of the gas and the air and further enhance the combustion rate of the gas.
In this scheme, lobe mixing device simple structure, easily processing. The lobe blender is based on the swirl motion theory, and the swirl that its produced interacts with the mainstream, has increased the dwell time of a gas in afterburning room, and then has improved combustion efficiency.
The lobe mixer is arranged in the air inlet channel, so that the turbulence degree of gas and air can be increased, the turbulence transportation and mixing effects of the gas are further improved, and the erosion of high-temperature gas can be reduced. The lobe blender is arranged to have low resistance to ram air and low total pressure loss, thereby improving the overall performance of the engine.
Further, the first splitter plate and the second splitter plate are both trapezoidal in shape.
Furthermore, the smaller edges of the first flow dividing plate and the second flow dividing plate are top edges and are fixed on the flow dividing bent plate.
Further, the included angle is 22 °.
Further, the second flow distribution plate is arranged along the tangential direction of the flow distribution bent plate.
Further, the first splitter plate is located inside the bend of the splitter bend plate.
Furthermore, the first splitter plate and the second splitter plate positioned in the middle part are isosceles trapezoids; the first flow distribution plate and the second flow distribution plate on the edges are in a right-angled trapezoid shape, and the inclined edge is close to the first flow distribution plate or the second flow distribution plate in the middle.
Furthermore, the number of the first splitter plate and the second splitter plate is two.
Furthermore, the solid rocket ramjet also comprises an afterburning chamber, wherein one end of the afterburning chamber is provided with a primary fuel gas inlet pipe, and the other end of the afterburning chamber is provided with a spray pipe; the air inlet passage penetrates through the outer wall of the afterburning chamber, and is close to one side of the primary gas inlet pipe.
Furthermore, the intake duct includes return bend and connecting pipe, and the one end of return bend is fixed to run through and is set up on afterburning chamber's outer wall, and the other end is connected with the connecting pipe, and lobe blender setting is in the return bend.
In addition to the technical problems addressed by the present invention, the technical features constituting the technical solutions, and the advantageous effects brought by the technical features of the technical solutions described above, other technical problems that the present invention can solve, other technical features included in the technical solutions, and advantageous effects brought by the technical features will be described in further detail in the detailed description.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic diagram of an enhanced blending apparatus for a solid rocket ramjet according to the present invention.
FIG. 2 is a front view of an enhanced blending apparatus for a solid rocket ramjet according to the present invention.
Figure 3 is a schematic diagram of a lobe blender according to the present invention.
Figure 4 is a front view of a lobe blender according to the present invention.
Figure 5 is a left side view of the lobe blender of the present invention.
FIG. 6 is a graph of combustion efficiency for the present invention.
Wherein: 1. a primary gas inlet pipe; 2. an air inlet channel; 3. a lobe blender; 301. a shunt bending plate; 302. a first splitter plate; 303. a curved plate; 304. a second splitter plate; 4. a afterburning chamber; 5. and (4) a spray pipe.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, the invention provides an enhanced mixing device for a solid rocket ramjet, which comprises an afterburning chamber 4, wherein one end of a primary gas inlet pipe 1 is welded in the middle of one end of the afterburning chamber 4 in a penetrating manner, and one end of a spray pipe 5 is welded in the middle of the other end of the afterburning chamber 4 in a penetrating manner; the nozzle 5 is of the convergent-divergent type. The air inlet channel 2 penetrates through the outer wall of the afterburning chamber 4, and the air inlet channel 2 is close to one side of the primary gas inlet pipe 1; the inlet channel 2 comprises an elbow and a connecting pipe, one end of the elbow is welded on the outer wall of the afterburning chamber 4 in a penetrating mode, the other end of the elbow is connected with the connecting pipe with the same diameter in a welding mode, and the lobe blender 3 is arranged in the elbow.
The lobe blender 3 comprises a flow dividing bent plate 301 and a lobe body, wherein the side surface of the flow dividing bent plate 301 is welded on the inner wall of the air inlet channel 2; the lobe body includes at least a first splitter plate 302 and a second splitter plate 304.
Specifically, the number of the first splitter plate 302 and the second splitter plate 304 is two; the first splitter plate 302 and the second splitter plate 304 in the middle are isosceles trapezoids; the first and second flow distribution plates 302 and 304 at the edges are right trapezoid, and the oblique side is close to the first or second flow distribution plate 302 or 304 at the middle.
The first splitter plate 302 and the second splitter plate 304 are connected by a curved plate 303; the top edges of the first flow dividing plate 302, the curved plate 303 and the second flow dividing plate 304 are smaller edges, and are welded on the lower edges of the flow dividing curved plate 301 in sequence, and the bottom edges are connected in sequence to form a rectangular corrugated shape. Referring to fig. 1, two first flow dividing plates 302 and two second flow dividing plates 304 are connected by three curved plates 303, and the curved plates 303 are connected with the first flow dividing plate 302 or the second flow dividing plate 304 by welding. The curved plate 303, the first flow dividing plate 302, and the second flow dividing plate 304 are connected to the curved plate 301 by welding.
The bottom angle of the first current splitter plate 302 coincides with the bottom angle projection of the adjacent second current splitter plate 304, and the plate surface projections of the first current splitter plate 302 and the second current splitter plate 304 form an included angle. The second shunting plate 304 is arranged along the tangential direction of the shunting bent plate 301; the first splitter plate 302 is located inside the bend of the splitter curved plate 301.
The principle is as follows: the bottom edges of the first splitter plate 302, the second splitter plate 304 and the curved plate 303 form a rectangular corrugation, and the air generates spanwise vortices caused by kelvin-helmholtz instability at the rectangular corrugation of the lobe blender 3, and induces generation of flow-direction vortices, so that the formed spanwise vortices and flow-direction vortices enhance the turbulence and vorticity of the gas and the air compared with the background, enhance the blending of the gas and the air, and further enhance the combustion rate of the gas.
The lobe mixing device is simple in structure and easy to process. The lobe blender 3 is based on the swirl motion theory, and the swirl that its produced interacts with the mainstream, has increased the dwell time of a gas in afterburning chamber 4, and then has improved combustion efficiency.
The lobe blender 3 is arranged in the air inlet channel 2, so that the turbulence degree of gas and air can be increased, the turbulence transportation and blending effects of the gas are further improved, and the erosion of high-temperature gas can be reduced. The lobe blender 3 is arranged to have low resistance to ram air and low total pressure loss, thereby improving the overall performance of the engine.
In the scheme, the lobe blender 3 comprises a first flow channel and a second flow channel, wherein air passes through the inner wall of the air inlet 2, the first flow dividing plate 302 and the curved plate 303 to form the first flow channel, or the air passes through the first flow dividing plate 302 and the two curved plates 303 to form the first flow channel; the air passes over the upper surface of the second manifold plate 304 to form a second flow path.
Air enters from the air inlet channel 2 and flows into the first flow channel and the second flow channel through the lobe blender 3, the flow areas of the first flow channel and the second flow channel are different, so that the air in the first flow channel and the air in the second flow channel generate a speed difference and a pressure difference, and the speed difference and the pressure difference drive and enhance the blending process. The lobe blender 3 divides ram air into two paths to enter the afterburning chamber 4, so that the characteristic requirements of high-temperature ignition and oxygen-enriched combustion of the boron-containing primary fuel gas are met.
According to the embodiment of the invention, the working conditions of 25km of flight height and 4Ma of flight speed are taken as examples, the included angle is 22 degrees, the speed difference of ram air formed in the second flow channel and the first flow channel is 270m/s, the pressure difference is 10000Pa, the mixing and combustion of air and fuel gas in the afterburning chamber 4 are finally enhanced, and compared with the condition that a lobe mixer 3 is not arranged in the air inlet channel 2, the combustion efficiency is improved by 5.7%.
The performance of the solid rocket ramjet with or without the wave lobe blender 3 is calculated, the calculation result is shown in fig. 6, wherein the abscissa represents the distance from the calculated section to the head of the afterburning chamber 4, and the ordinate represents the characteristic speed combustion efficiency, and the result shows that the enhanced blending device provided by the embodiment of the invention can obviously improve the combustion efficiency in the afterburning chamber 4 of the engine.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. An enhanced mixing device for a solid rocket ramjet, which comprises an air inlet channel (2), characterized in that a lobe mixer (3) is arranged in the air inlet channel (2),
the lobe blender (3) comprises a flow dividing bent plate (301) and a lobe body, wherein the flow dividing bent plate (301) is fixed on the inner wall of the air inlet channel (2);
the lobe body comprises at least one first flow dividing plate (302), a curved plate (303) and a second flow dividing plate (304), and the first flow dividing plate (302) and the second flow dividing plate (304) are connected through the curved plate (303); the top edges of the first flow dividing plate (302), the curved plate (303) and the second flow dividing plate (304) are all fixed on the flow dividing bent plate (301) in sequence, and the bottom edges are connected in sequence and then are in a rectangular corrugated shape; the plate surface projection of the first splitter plate (302) and the second splitter plate (304) forms an included angle.
2. The enhanced blending apparatus for a solid rocket ramjet according to claim 1, wherein said first splitter plate (302) and said second splitter plate (304) are both trapezoidal in shape.
3. The enhanced blending apparatus for a solid rocket ramjet according to claim 2, wherein the smaller sides of the first splitter plate (302) and the second splitter plate (304) are top sides and are fixed on the splitter plate (301).
4. The enhanced blending apparatus for a solid rocket ramjet according to claim 3, wherein said included angle is 22 °.
5. The enhanced blending apparatus for a solid rocket ramjet according to claim 4, wherein said second splitter plate (304) is arranged along a tangential direction of the splitter plate (301).
6. The enhanced blending apparatus for a solid rocket ramjet according to claim 5, wherein said first splitter plate (302) is located inside the curve of the splitter plate (301).
7. The enhanced dilution apparatus for a solid-rocket ramjet according to claim 2 or 6, wherein the first and second splitter plates (302, 304) located in the middle portion are isosceles trapezoids; the first flow dividing plate (302) and the second flow dividing plate (304) at the edge are in a right trapezoid shape, and the inclined edge is close to the first flow dividing plate (302) or the second flow dividing plate (304) at the middle part.
8. The enhanced blending apparatus for a solid rocket ramjet according to claim 7, wherein the number of said first splitter plate (302) and said second splitter plate (304) is two.
9. The enhanced blending device for a solid rocket ramjet according to claim 8, wherein said solid rocket ramjet further comprises an afterburning chamber (4), one end of said afterburning chamber (4) is provided with a primary gas inlet pipe (1), and the other end is provided with a nozzle (5); the air inlet channel (2) penetrates through the outer wall of the afterburning chamber (4), and the air inlet channel (2) is close to one side of the primary gas inlet pipe (1).
10. The enhanced mixing device for the solid rocket ramjet according to claim 9, wherein the inlet channel (2) comprises an elbow and a connecting pipe, one end of the elbow is fixedly arranged on the outer wall of the afterburner (4) in a penetrating way, the other end of the elbow is connected with the connecting pipe, and the lobe mixer (3) is arranged in the elbow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111104516.7A CN113700574B (en) | 2021-09-22 | 2021-09-22 | A reinforcing mixing device for solid rocket ramjet |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111104516.7A CN113700574B (en) | 2021-09-22 | 2021-09-22 | A reinforcing mixing device for solid rocket ramjet |
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| CN113700574A true CN113700574A (en) | 2021-11-26 |
| CN113700574B CN113700574B (en) | 2022-09-27 |
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| Application Number | Title | Priority Date | Filing Date |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114352437A (en) * | 2022-01-07 | 2022-04-15 | 北京理工大学 | Solid fuel stamping combined engine suitable for wide Mach number flight |
| CN114837849A (en) * | 2022-05-10 | 2022-08-02 | 南京航空航天大学 | Powder-liquid stamping combined engine and control method |
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| US6233920B1 (en) * | 1999-02-01 | 2001-05-22 | Stage Iii Technologies, L.C. | Contoured thrust reverser and lobed nozzle noise suppressor for gas turbine engines |
| CN105402048A (en) * | 2015-11-30 | 2016-03-16 | 南京航空航天大学 | Low infrared signature lobe injection mixing device used for two-dimensional nozzle outlet |
| CN106123031A (en) * | 2015-05-08 | 2016-11-16 | 安萨尔多能源瑞士股份公司 | Hybrid system |
| CN107620653A (en) * | 2017-09-27 | 2018-01-23 | 西北工业大学 | A kind of disturbing flow device for solid-rocket combustion gas scramjet engine |
| CN112747335A (en) * | 2021-01-06 | 2021-05-04 | 中国人民解放军国防科技大学 | Lobe type backward step structure, lobe type concave cavity device and afterburning chamber |
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2021
- 2021-09-22 CN CN202111104516.7A patent/CN113700574B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6233920B1 (en) * | 1999-02-01 | 2001-05-22 | Stage Iii Technologies, L.C. | Contoured thrust reverser and lobed nozzle noise suppressor for gas turbine engines |
| CN106123031A (en) * | 2015-05-08 | 2016-11-16 | 安萨尔多能源瑞士股份公司 | Hybrid system |
| CN105402048A (en) * | 2015-11-30 | 2016-03-16 | 南京航空航天大学 | Low infrared signature lobe injection mixing device used for two-dimensional nozzle outlet |
| CN107620653A (en) * | 2017-09-27 | 2018-01-23 | 西北工业大学 | A kind of disturbing flow device for solid-rocket combustion gas scramjet engine |
| CN112747335A (en) * | 2021-01-06 | 2021-05-04 | 中国人民解放军国防科技大学 | Lobe type backward step structure, lobe type concave cavity device and afterburning chamber |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114352437A (en) * | 2022-01-07 | 2022-04-15 | 北京理工大学 | Solid fuel stamping combined engine suitable for wide Mach number flight |
| CN114837849A (en) * | 2022-05-10 | 2022-08-02 | 南京航空航天大学 | Powder-liquid stamping combined engine and control method |
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| CN113700574B (en) | 2022-09-27 |
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