CN213300150U - Rotary detonation combustion chamber capable of realizing observation of flow field structure of isolation section - Google Patents
Rotary detonation combustion chamber capable of realizing observation of flow field structure of isolation section Download PDFInfo
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- CN213300150U CN213300150U CN202020612501.6U CN202020612501U CN213300150U CN 213300150 U CN213300150 U CN 213300150U CN 202020612501 U CN202020612501 U CN 202020612501U CN 213300150 U CN213300150 U CN 213300150U
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- 238000005474 detonation Methods 0.000 title claims abstract description 104
- 238000002955 isolation Methods 0.000 title claims abstract description 83
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 52
- 239000000446 fuel Substances 0.000 claims abstract description 52
- 230000003287 optical effect Effects 0.000 claims abstract description 29
- 238000002156 mixing Methods 0.000 claims abstract description 25
- 238000002347 injection Methods 0.000 claims abstract description 24
- 239000007924 injection Substances 0.000 claims abstract description 24
- 239000005304 optical glass Substances 0.000 claims abstract description 9
- 239000011229 interlayer Substances 0.000 claims description 9
- 239000007921 spray Substances 0.000 abstract description 6
- 230000035939 shock Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 8
- 230000008859 change Effects 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000007704 transition Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005352 clarification Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000000644 propagated effect Effects 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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Abstract
The utility model relates to the technical field of engines, and discloses a rotary detonation combustor capable of realizing observation of a flow field structure of an isolation section, which mainly comprises a rotary detonation combustor and an air inlet mixing module; the air intake mixing module is of a hollow sandwich structure and comprises a radial runway type air intake section, a radial runway type isolation section and a fuel injection module; the incoming air is accelerated by the radial runway type air inlet section supersonic speed spray pipe to form supersonic speed airflow which enters the radial runway type isolation section and is mixed with fuel to form combustible gas; the high-speed combustible gas is detonated in the combustion chamber and forms high-frequency high-pressure rotary detonation waves, and the high-frequency high-pressure rotary detonation waves disturb incoming flow and form shock wave structures and are transmitted to the radial runway type isolation section in advance. Optical glass is respectively arranged on two sides of a flow channel of the radial runway type isolation section, corresponding optical observation equipment is arranged on two sides of the optical glass, and an observation light path passes through the flow field of the isolation section through the optical glass, so that optical observation on the wave system structure of the flow field of the isolation section is realized.
Description
Technical Field
The utility model relates to the technical field of engines, concretely relates to can realize rotatory knocking combustion chamber of keeping apart section flow field structure observation.
Background
In the rotary detonation engine, rotary detonation waves are transmitted at high speed in a combustion chamber, the frequency reaches thousands of hertz, the peak value can reach several megapascals, and the pressure of the combustion chamber has obvious difference along the circumferential direction to form high-frequency periodic pulsating pressure. Such a complex and harsh combustion back pressure environment can affect the injection and mixing processes of the fuel and the oxidant. For a rotary detonation ramjet engine, this may directly affect the flow process at the inlet of the rotary detonation combustor, in severe cases causing air intake choking and causing misfire. For a rotary detonation rocket engine and a rotary detonation turbine engine, rotary detonation combustion back pressure is mutually coupled with flow, a mixing process and the like of a propellant, and has important influence on stable propagation of rotary detonation waves. Therefore, the research on interaction between the rotary detonation back pressure and incoming flow is carried out, the influence of the rotary detonation back pressure on the airflow of the isolation section is clarified, the wave system structure and the evolution characteristic of the wave system structure of the clarification isolation section along with propagation of the detonation wave are obtained, and the method has important significance for efficient and stable work of a rotary detonation engine, especially a rotary detonation ramjet.
In the prior art, an isolation section is generally adopted to isolate the influence of the rotary detonation back pressure on the incoming flow of the air inlet channel. The current rotary detonation combustion chamber configurations are mainly divided into two types, namely a disc shape and a circular shape (the cylinder shape is a special configuration of the circular shape and has no inner column). In the working process of the rotary detonation engine, the peak pressure of the detonation wave is up to several megapascals and is propagated along the circumferential direction of the combustion chamber at high frequency, and the strong pressure disturbance caused by the high-frequency pressure disturbance can inevitably cause the change of the flow state of the inflow at the inlet of the combustion chamber, and a complex wave system structure is formed in the isolation section. The method is very important for the research of the isolated section wave system structure, but at present, no effective method is available for realizing the direct observation of the isolated section wave system structure of the rotary detonation engine.
SUMMERY OF THE UTILITY MODEL
Based on the problems, the utility model provides a rotary detonation combustor capable of realizing the observation of the flow field structure of the isolation section, which is beneficial to the arrangement of the observation light path and the arrangement of the optical observation equipment by arranging the flow channel of the isolation section perpendicular to the axial direction of the combustor; meanwhile, a runway-type rotary detonation combustion chamber structure is adopted, and the flow area of the isolation section in the equal straight section along the radial direction does not change, so that the stable state of airflow in the isolation section is ensured. The configuration can realize optical observation of the flow field structure of the isolation section of the rotary detonation engine under the supersonic incoming flow condition, and provides a scheme for optical observation of the isolation section of the rotary detonation ramjet engine.
In order to solve the technical problems, the utility model provides a rotary detonation combustor capable of realizing the observation of a flow field structure of an isolation section, which mainly comprises the rotary detonation combustor and an air inlet mixing module arranged at the inlet end of the rotary detonation combustor, wherein the air inlet mixing module is vertical to the central axis of the rotary detonation combustor; the cross section of the rotary detonation combustor is mainly of a runway-shaped structure formed by two opposite semicircular parts and a runway-shaped equal-straight section connecting the two semicircular parts; the air intake mixing module is of a hollow sandwich structure and comprises a radial runway type air intake section, a radial runway type isolation section and a fuel injection module, wherein the radial runway type air intake section, the radial runway type isolation section and the fuel injection module are positioned on the same central axis with the rotary detonation combustion chamber; the outlet end of the radial runway type isolation section is communicated with the inner cavity of the rotary detonation combustor; the side surface position of the air inlet mixing module corresponding to the radial runway type isolation section is an optical observation area, and two side walls of the radial runway type isolation section corresponding to the optical observation area are made of optical glass; one of a schlieren observation device, a shadow observation device or a photographic device is arranged on two sides of the optical observation area.
Further, a switching section which turns the airflow flowing in the radial direction to flow in the axial direction of the rotary detonation combustion chamber is arranged between the outlet end of the radial runway type isolation section and the inlet end of the rotary detonation combustion chamber.
Further, the fuel injection position of the fuel injection module is located at the outlet end of the radial runway type isolation section or the radial runway type isolation section and the area expansion section of the rotary detonation combustor.
Further, the fuel injection module comprises a fuel cavity and a plurality of fuel injection holes, and the fuel injection holes are communicated with the fuel cavity and the outlet end of the radial runway type isolation section.
Further, the fuel cavity is located on the inner side of the radial runway type air inlet section and close to the center of the air inlet mixing module.
Furthermore, an inner column I is arranged in the rotary detonation combustion chamber, and a runway-type interlayer flow channel with parallel wall surfaces is formed by the outer wall of the inner column I and the inner wall of the rotary detonation combustion chamber.
Furthermore, the fuel cavity is of a runway-shaped annular cavity structure, and the radial runway-shaped air inlet section is positioned on the inner side of the fuel cavity and close to the center of the air inlet mixing module; the rotary detonation combustion chamber is of a runway-type interlayer tubular structure with an inner barrel, and the inner wall of the rotary detonation combustion chamber and the inner barrel form a runway-type interlayer flow channel with parallel wall surfaces.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model arranges the flow passage of the isolation section perpendicular to the axial direction of the combustion chamber, which is beneficial to the arrangement of the observation light path and the arrangement of the optical observation equipment; meanwhile, a runway-type rotary detonation combustion chamber structure is adopted, and the flow area of the isolation section in the equal straight section along the radial direction does not change, so that the stable state of airflow in the isolation section is ensured. The configuration can realize optical observation of the flow field structure of the isolation section of the rotary detonation engine under the supersonic incoming flow condition, and provides a scheme for optical observation of the isolation section of the rotary detonation ramjet engine.
Drawings
FIG. 1 is a schematic structural diagram of an outer diameter air intake annular combustion chamber capable of realizing observation of a flow field structure of an isolation section under rotary detonation back pressure in embodiment 1;
FIG. 2 is a schematic view of the cross-sectional structure of the flowpath of FIG. 1 taken along a semicircular portion in a radial direction;
FIG. 3 is a schematic structural view of an intake cylindrical combustion chamber having an outer diameter according to another embodiment 1;
FIG. 4 is a schematic view of the cross-sectional structure of the flowpath of FIG. 3 taken along a semicircular portion in a radial direction;
FIG. 5 is a schematic structural diagram of an inner diameter gas intake annular combustion chamber capable of realizing observation of a flow field structure of an isolation section under rotary detonation back pressure in embodiment 2;
FIG. 6 is a schematic view of the flowpath cross-sectional configuration of FIG. 5 taken along a radial direction of a semicircular portion;
FIG. 7 is a schematic diagram of an observation optical path arrangement of an isolation band wave system in examples 1 and 2;
wherein: 1. a radial runway type air intake section; 2. a radial runway type isolation section; 3. a rotary detonation combustor; 4. a semi-circular portion; 5. a runway type equal straight section; 6. an optical observation area; 7. a switching section; 8. a fuel chamber; 9. a fuel injection hole; 10. a first inner column; 11. an inner barrel; 12. a light source; 13. a concave reflector; 14. a plane mirror; 15. an optical glass; 16. a knife edge; 17. a focusing lens; 18. high speed cameras.
Detailed Description
To make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the following examples and drawings, and the exemplary embodiments and descriptions thereof of the present invention are only used for explaining the present invention, and are not intended as limitations of the present invention.
Example 1:
referring to fig. 1, 2 and 7, a rotary detonation combustion chamber capable of realizing observation of a flow field structure of an isolation section mainly comprises a rotary detonation combustion chamber 3 and an air inlet blending module arranged at an inlet end of the rotary detonation combustion chamber 3, wherein the air inlet blending module is vertical to a central axis of the rotary detonation combustion chamber 3; the cross section of the rotary detonation combustor 3 is mainly of a runway-shaped structure formed by two opposite semicircular parts 4 and a runway-shaped equal straight section 5 connecting the two semicircular parts 4; the air intake mixing module is of a hollow sandwich structure and comprises a radial runway type air intake section 1, a radial runway type isolation section 2 and a fuel injection module, wherein the radial runway type air intake section 1 and the radial runway type isolation section 2 are positioned on the same central axis with the rotary detonation combustor 3; the outlet end of the radial runway type isolation section 2 is communicated with the inner cavity of the rotary detonation combustor 3; the side position of the air inlet mixing module corresponding to the radial runway type isolation section 2 is an optical observation area 6, and two side walls of the radial runway type isolation section 2 corresponding to the optical observation area 6 are made of optical glass 15; one of a schlieren observing device, a shadow observing device or a photographing device is arranged on both sides of the optical observation area 6.
In the present embodiment, in the circumferential direction, the combustion chamber may be divided into three sections: the runner type equal straight section 5 and the two semicircular parts 4 are respectively positioned at two sides of the runner type equal straight section 5, and the three parts have the same flow channel configuration along the radial direction, so that smooth transition between the two semicircular parts 4 and the flow channel of the runner type equal straight section 5 is realized. The incoming air enters the radial runway type air inlet section 1 from the external channel, is accelerated to supersonic velocity (Ma >1) under the acceleration of the supersonic velocity spray pipe of the radial runway type air inlet section 1, and then enters the radial runway type isolation section 2 (an optical observation area 6 area). The fuel is sprayed into the outlet end of the radial runway type isolation section 2 through the fuel injection module, the fuel enters the runner and is mixed with incoming air to enter the rotary detonation combustor 3 at the outlet end of the radial runway type isolation section 2, combustible mixed gas is detonated in the combustor to form high-frequency rotary detonation waves propagating along the circumferential direction, and detonation combustion products are discharged from the outlet of the combustor at a high speed along the axial direction, so that thrust is generated. The detonation wave pressure in the combustion chamber is higher, so that the airflow of the radial runway type isolation section 2 is influenced, and a specific forward shock wave is formed in the radial runway type isolation section 2.
Radial runway type air inlet section 1, radial runway type isolation section 2, fuel cavity 8 and rotatory detonation combustor 3's the central axis is located same straight line in this embodiment, guarantees that radial runway type isolation section 2 runner is perpendicular with combustor axial direction, is favorable to light path arrangement and optical equipment's putting. And in the radial runner type isolation section 2 part of the two semicircular parts 4, airflow flows along the radial direction, and the influence of curvature causes additional area change of the radial isolation section runner, so that the airflow has certain influence on state parameters such as the Mach number and the like, and the quantitative research is not facilitated. Based on this, the runway-type equal straight section 5 designed in this embodiment has no extra area change caused by curvature when the airflow flows along the radial direction, and can maintain specific airflow parameters such as mach number, pressure and temperature; the flow area of the isolation section in the equal straight section along the radial direction does not change, thereby ensuring the stable state of the airflow in the isolation section. In addition, the two side wall surfaces of the runway type equal straight section 5 are parallel to each other and vertical to the flow direction of the air flow, so that the arrangement of an optical observation window is facilitated. And through an optical observation window, schlieren and shadow observation can be carried out, and further the radial runway type isolation section 2 wave system structure under the influence of the rotation detonation is obtained. In this embodiment, a schlieren observation optical path is taken as an example, a schematic diagram of an optical path layout is shown in fig. 7, light emitted by a light source 12 irradiates on a concave reflector 13, and is reflected to a plane reflector 14 by the concave reflector 13, the plane reflector 14 is installed at two sides of a runway-shaped equal straight section 5 of a radial runway-shaped isolation channel, the plane reflector 14 at one side irradiates the light source 12 into the isolation channel through an optical glass 15, under the condition of air flow in the isolation channel, the light passes through the isolation channel to generate a shadow or schlieren effect, and is transmitted to a focusing lens 17 through the plane reflector 14 at the other side, the concave reflector 13 and a knife edge 16 slit, and the focused light enters a high-speed camera 18 to realize observation of the shadow or schlieren generated by the air flow in the isolation channel.
And a transition section 7 for turning the radially flowing airflow to the axially flowing rotating detonation combustor 3 is arranged between the outlet end of the radial runway type isolation section 2 and the inlet end of the rotating detonation combustor 3. The adapter section 7 has two functions, namely: the radial flow airflow is diverted to the combustion chamber to flow axially; the second action is as follows: a fuel injection module is arranged. In the embodiment, the fuel injection position of the fuel injection module is positioned at the outlet end of the radial runway type isolation section 2 or the area expansion section of the radial runway type isolation section 2 and the rotary detonation combustor 3.
The fuel injection module comprises a fuel cavity 8 and a plurality of fuel spray holes 9, and the fuel spray holes 9 are communicated with the fuel cavity 8 and the outlet end of the radial runway type isolation section 2; the fuel cavity 8 in this embodiment is located inside the radial runway type air intake section 1 and near the center of the air intake blend module. The air inlet channel is arranged at the periphery of the fuel cavity 8, and the outer diameter air inlet is realized. An inner column I10 is arranged in the rotary detonation combustion chamber 3, a runway type interlayer flow channel with parallel wall surfaces is formed by the outer wall of the inner column I10 and the inner wall of the rotary detonation combustion chamber 3, the rotary detonation combustion chamber 3 is of a similar annular runway structure, and an outer diameter air inlet annular combustion chamber configuration scheme (as shown in figures 1 and 2) can be formed. In addition, in the case of no inner post 10, the combustion chamber has a cylindrical-like racetrack structure, and a cylindrical combustion chamber configuration scheme with an outer diameter of air inlet can be formed (as shown in fig. 3 and 4).
Example 2:
referring to fig. 5, 6 and 7, a rotary detonation combustor capable of realizing observation of a flow field structure of an isolation section mainly comprises a rotary detonation combustor 3 and an air intake blending module arranged at an inlet end of the rotary detonation combustor 3, wherein the air intake blending module is perpendicular to a central axis of the rotary detonation combustor 3; the cross section of the rotary detonation combustor 3 is mainly of a runway-shaped structure formed by two opposite semicircular parts 4 and a runway-shaped equal straight section 5 connecting the two semicircular parts 4; the air intake mixing module is of a hollow sandwich structure and comprises a radial runway type air intake section 1, a radial runway type isolation section 2 and a fuel injection module, wherein the radial runway type air intake section 1 and the radial runway type isolation section 2 are positioned on the same central axis with the rotary detonation combustor 3; the outlet end of the radial runway type isolation section 2 is communicated with the inner cavity of the rotary detonation combustor 3; the side position of the air inlet mixing module corresponding to the radial runway type isolation section 2 is an optical observation area 6, and two side walls of the radial runway type isolation section 2 corresponding to the optical observation area 6 are made of optical glass 15; one of a schlieren observing device, a shadow observing device or a photographing device is arranged on both sides of the optical observation area 6.
The fuel injection module comprises a fuel cavity 8 and a plurality of fuel spray holes 9, and the fuel spray holes 9 are communicated with the fuel cavity 8 and the outlet end of the radial runway type isolation section 2; the central axes of the radial runway type air inlet section 1, the radial runway type isolation section 2, the fuel cavity 8 and the rotary detonation combustor 3 are positioned on the same straight line.
The fuel cavity 8 is of a runway-shaped annular cavity structure, and the radial runway-shaped air inlet section 1 is positioned on the inner side of the fuel cavity 8 and close to the center of the air inlet mixing module; the rotary detonation combustion chamber 3 is of a runway-type interlayer tubular structure with an inner barrel 11, and the inner wall of the rotary detonation combustion chamber 3 and the inner barrel 11 form a runway-type interlayer flow channel with parallel wall surfaces; namely, the air inlet channel is arranged in the inner periphery of the combustion cavity, the rotary detonation combustion chamber 3 is of a similar annular runway structure, the inner diameter air inlet annular combustion chamber configuration scheme can be formed, and the effective arrangement of the optical observation area 6 is ensured.
Other parts in this embodiment are the same as embodiment 1, and are not described herein again.
The embodiment of the present invention is the above. The specific parameters in the above embodiments and examples are only for the purpose of clearly showing the verification process of the present invention, and are not used to limit the protection scope of the present invention, which is still subject to the claims, and all the equivalent structural changes made by using the contents of the specification and drawings of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The utility model provides a can realize rotatory detonation combustor of isolation section flow field structure observation which characterized in that: the device mainly comprises a rotary detonation combustion chamber (3) and an air intake mixing module arranged at the inlet end of the rotary detonation combustion chamber (3), wherein the air intake mixing module is vertical to the central axis of the rotary detonation combustion chamber (3); the cross section of the rotary detonation combustor (3) is mainly of a runway-shaped structure formed by two semicircular parts (4) arranged oppositely and a runway-shaped equal straight section (5) connecting the two semicircular parts (4); the air intake mixing module is of a hollow sandwich structure and comprises a radial runway type air intake section (1), a radial runway type isolation section (2) and a fuel injection module, wherein the radial runway type air intake section and the radial runway type isolation section are positioned on the same central axis of the rotary detonation combustion chamber (3); the outlet end of the radial runway type isolation section (2) is communicated with the inner cavity of the rotary detonation combustion chamber (3); the lateral surface position of the air inlet mixing module corresponding to the radial runway type isolation section (2) is an optical observation area (6), and two side walls of the radial runway type isolation section (2) corresponding to the optical observation area (6) are made of optical glass (15); and one of a schlieren observation device, a shadow observation device or a photographic device is arranged on two sides of the optical observation area (6).
2. The rotary detonation combustor of claim 1, wherein the rotary detonation combustor is configured to achieve isolated section flow field structure observation, and wherein: and a switching section (7) for turning the radially flowing airflow to the axial flow of the rotary detonation combustion chamber (3) is arranged between the outlet end of the radial runway type isolation section (2) and the inlet end of the rotary detonation combustion chamber (3).
3. The rotary detonation combustor of claim 1, wherein the rotary detonation combustor is configured to achieve isolated section flow field structure observation, and wherein: and the fuel injection position of the fuel injection module is positioned at the outlet end of the radial runway type isolation section (2) or the area expansion section of the radial runway type isolation section (2) and the rotary detonation combustor (3).
4. The rotary detonation combustor of any one of claims 1-3, wherein the rotary detonation combustor is configured to enable observation of isolated section flow field structures, and is characterized in that: the fuel injection module comprises a fuel cavity (8) and a plurality of fuel injection holes (9), and the fuel injection holes (9) are communicated with the fuel cavity (8) and the outlet end of the radial runway type isolation section (2).
5. The rotary detonation combustor of claim 4, wherein the rotary detonation combustor is configured to achieve isolated section flow field structure observation, and wherein: the fuel cavity (8) is positioned at the inner side of the radial runway type air inlet section (1) and is close to the center of the air inlet mixing module.
6. The rotary detonation combustor of claim 5, wherein the rotary detonation combustor is configured to achieve isolated section flow field structure observation, and wherein: an inner column I (10) is arranged in the rotary detonation combustion chamber (3), and the outer wall of the inner column I (10) and the inner wall of the rotary detonation combustion chamber (3) form a runway-shaped interlayer flow channel with parallel wall surfaces.
7. The rotary detonation combustor of claim 4, wherein the rotary detonation combustor is configured to achieve isolated section flow field structure observation, and wherein: the fuel cavity (8) is of a runway-type annular cavity structure, and the radial runway-type air inlet section (1) is positioned on the inner side of the fuel cavity (8) and close to the center of the air inlet mixing module; the rotary detonation combustor (3) is of a runway type interlayer tubular structure with an inner barrel (11), and the inner wall of the rotary detonation combustor (3) and the inner barrel (11) form a runway type interlayer flow channel with parallel wall surfaces.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020612501.6U CN213300150U (en) | 2020-04-22 | 2020-04-22 | Rotary detonation combustion chamber capable of realizing observation of flow field structure of isolation section |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020612501.6U CN213300150U (en) | 2020-04-22 | 2020-04-22 | Rotary detonation combustion chamber capable of realizing observation of flow field structure of isolation section |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114427689A (en) * | 2022-01-20 | 2022-05-03 | 中国空气动力研究与发展中心空天技术研究所 | Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation |
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2020
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114427689A (en) * | 2022-01-20 | 2022-05-03 | 中国空气动力研究与发展中心空天技术研究所 | Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation |
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Granted publication date: 20210528 |