CN210513708U - Ground test model for supersonic combustion foundation research - Google Patents
Ground test model for supersonic combustion foundation research Download PDFInfo
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- CN210513708U CN210513708U CN201921303120.3U CN201921303120U CN210513708U CN 210513708 U CN210513708 U CN 210513708U CN 201921303120 U CN201921303120 U CN 201921303120U CN 210513708 U CN210513708 U CN 210513708U
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Abstract
The utility model provides a ground test model for supersonic combustion foundation research, the model comprises an isolation section, a windowing combustion section, an expansion section and a water component detection module, a supersonic airflow channel is arranged in the model, and the supersonic airflow channel sequentially penetrates through the isolation section, the windowing combustion section and the expansion section; the isolation section comprises an isolation section frame and a first side face assembly, the first side face assembly is arranged on the side face of the isolation section frame, mounting holes are formed in the top and the bottom of the isolation section frame, and the isolation assembly is mounted in the mounting holes. The utility model provides a ground test model for supersonic combustion foundation research, parts such as fuel injection, ignition, flame stability in the experiment all adopt the modularized design, can satisfy the nimble quick replacement of each functional unit in the process of the test, save the test cost, improve test efficiency.
Description
Technical Field
The utility model relates to an aerospace field specifically is a ground test model for supersonic combustion foundation research.
Background
The supersonic combustion organization technology is the key for realizing the engineering of the scramjet engine. The main problem to be solved by the technology of the scramjet engine combustion chamber is to realize the injection, atomization, evaporation, mixing, ignition and stable combustion of fuel in limited space (meter level), time (millisecond level) and high-speed airflow (usually supersonic airflow), convert chemical energy into heat energy to the maximum extent, ensure high thermal efficiency and small pressure loss, and adapt to wide fuel/air equivalence ratio change, pressure change and speed change of the combustion chamber so as to meet the requirements of flying, accelerating, cruising and the like of an aircraft in different airspaces and at different speeds. Therefore, the physical mechanism of the supersonic combustion is of great value to the optimal design of the scramjet engine. In order to simulate the physical mechanism of supersonic combustion under the ground test condition, on one hand, a supersonic airflow needs to be provided for simulating the airflow state of an engine under the actual working condition, and on the other hand, a fuel supply system needs to be equipped for the injection combustion of fuel. When the supersonic combustion process is combusted under the ground condition, a large number of tests are required to be carried out, and various possible influence factors are analyzed. The testing process involves a number of changes and modifications to the test hardware.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a ground test model for supersonic combustion foundation research has reduced the reprocess of large-scale dysmorphism experiment piece, has saved experiment processing cost, improves experimental efficiency.
The utility model discloses a following technical scheme realizes:
the utility model provides a ground test model for supersonic combustion foundation research, the model comprises an isolation section, a windowing combustion section, an expansion section and a water component detection module, a supersonic airflow channel is arranged in the model, and the supersonic airflow channel sequentially penetrates through the isolation section, the windowing combustion section and the expansion section; the isolation section comprises an isolation section frame and a first side surface assembly, the first side surface assembly is arranged on the side surface of the isolation section frame, mounting holes are formed in the top and the bottom of the isolation section frame, and the isolation assembly is mounted in the mounting holes;
the windowing combustion section comprises a combustion chamber frame, a second side surface assembly arranged on the side surface of the combustion chamber frame and a top surface assembly arranged at the top of the isolation section frame; the dilating segment comprises a dilating segment frame;
the water component detection module comprises a first water component detection module and a second water component detection module, the first water component detection module is arranged at the front end of the isolation section, and the second water component detection module is arranged at the tail end of the expansion section;
the front end of the isolation section is connected with the first water component detection module, the rear end of the isolation section is connected with the front end of the windowing combustion section, the rear end of the windowing combustion section is connected with the front end of the expansion section, and the tail end of the expansion section is connected with the second water component detection module;
the supersonic air flow channel comprises a supersonic inlet and a supersonic outlet, the supersonic inlet is arranged at the front end of the first water component detection module, and the supersonic outlet is arranged at the tail end of the second water component detection module.
Optionally, the first side assembly is a first side window assembly;
the second side surface assembly is a second side window assembly, and the top surface assembly is a top window assembly.
Optionally, the first side window assembly and the second side window assembly have the same structure.
Optionally, the isolation component is an injection member, and the injection member is mounted in the mounting hole;
the injection member comprises: the size and the shape of the small support plate are matched with the mounting holes; one side of the large support plate, which is far away from the small support plate, is provided with an injection hole; the fuel injection device is characterized in that a fuel channel is arranged in the small support plate, a fuel nozzle is arranged on one side, away from the large support plate, of the small support plate, the injection hole, the fuel channel and the fuel nozzle are communicated with each other, and the fuel nozzle is communicated with the supersonic airflow channel.
Optionally, the top surface assembly is an injection member, a cavity is arranged at the top and the side of the combustion chamber frame, the injection member is installed in the cavity, and the isolation assembly is a blocking block.
Optionally, the top surface component is a top window block, a pressure measuring hole is arranged on the top window block, and the pressure measuring hole is connected with a pressure sensor.
Optionally, a cavity stabilizing area is formed at the lower part of the combustion chamber frame, and a slope is formed at one end of the cavity stabilizing area, which is close to the expansion section; two ignition position holes are formed at the lower end of the cavity stable area, and a sleeve is arranged in one ignition position hole to form a small ignition position hole.
Optionally, the expansion section frame is provided with a detection probe.
Optionally, the first side assembly is a side window block.
Optionally, the isolation assembly is a plugging block.
The beneficial effects of the utility model reside in that:
1. the utility model provides a ground test model for supersonic combustion foundation research, for the convenience of experimentation, each part adopts the modularized design, and each functional unit can change in a flexible way, has reduced the repeated processing of large-scale dysmorphism experiment piece, has saved the experiment processing cost, improves experimental efficiency.
2. The utility model discloses a scramjet combustor ground test model of supersonic combustion basic research can realize the selection of the various spouting positions of isolation section and the selection of spouting hole array position size. The jet mixing process of the fuel is observed using the first side window assembly of the isolation segment. The windowed combustion section is configured with a cavity stabilization zone and ignition site holes and is designed as a replaceable subassembly. The top surface assembly of the windowed combustion section can be provided with a top window block or a top window assembly. The quartz glass of the top window component can be used for projecting a laser sheet light source and irradiating trace particles of fuel, and after a light scattering effect is generated, the fuel distribution situation around the flame in the stable region of the concave cavity can be obtained by observing through the second side window component. The windowing combustion section can observe the ignition and flame stabilization processes through the second side window assembly, and can also be matched with the second side window assembly to carry out PLIF or PIV optical experimental measurement, or carry out schlieren measurement through double-sided windowing. Top window subassembly, second side window subassembly, integral erection are on the combustion chamber frame, convenient dismantlement, and the in-process of dismantling is difficult to bump garrulous glass. When the windowing component (the first side window component, the second side window component and the top window component) is used for fixing glass, the windowing component is fixed in a pressing mode and is separated from metal by an asbestos gasket, and glass is prevented from being crushed. The expansion section is provided with a detection probe arranged in a reverse mirror image mode, a laser emitting unit and a receiving unit for installing a discrete TDLAS probe. The discrete mounting holes are arranged on the expansion section in an aligned mode, and measurement at multiple positions can be achieved.
The whole combustion chamber is provided with a TDLAS integrated test module with an inlet and an outlet. And the inlet and outlet TDLAS integrated test module is connected with the integral model combustion chamber by a flange. The distribution of water composition or CO2 for the inlet and outlet is obtained, and the combustion efficiency of the combustion chamber can be converted by comparison.
The whole experimental part adopts the modularized design, and various functional parts required in the scramjet model combustion chamber are realized by adopting a mode of building blocks, so that the repeated processing of large-scale special-shaped experimental parts is reduced, the experimental processing cost is saved, and the experimental efficiency is improved.
3. In order to improve experimental efficiency, the utility model discloses carry out the modularized design to the test model to the functional component in the combustion chamber is constructed to the mode of taking building blocks, like spouting subassembly, first side window subassembly, second side window subassembly, side window sprue etc.. By designing an optimal basic component unit, it is possible to achieve the required functions with a minimum of replacement effort. Meanwhile, under the ground test condition, in order to detect the supersonic combustion process, temperature and pressure sensors can be adopted to detect the combustion airflow state. When basic research is carried out, in order to obtain more detailed information of supersonic combustion, optical diagnostic techniques, such as PIV, TDLAS, PLIF, etc., need to be adopted. The utility model discloses a second side window subassembly can be fine compatible with various optical measurement equipment on spatial arrangement, is convenient for develop various optical measurement.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only examples of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic diagram of a three-dimensional structure of a ground test model for basic research of supersonic combustion provided by an embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is an enlarged view of a portion of FIG. 1 at B;
FIG. 4 is an enlarged view of a portion of FIG. 1 at C;
FIG. 5 is a schematic diagram of a cross-sectional structure of a ground test model for basic research of supersonic combustion provided by an embodiment of the present invention;
FIG. 6 is an enlarged view of a portion of FIG. 5 at D;
FIG. 7 is a schematic structural diagram of an isolation section frame in an embodiment of the present invention;
fig. 8 is a schematic structural view of a first side window assembly in an embodiment of the present invention;
figure 9 is a schematic view of an injection member according to an embodiment of the invention;
FIG. 10 is a schematic view of a side window block according to an embodiment of the present invention;
fig. 11 is a schematic structural view of a leveling and plugging block in the embodiment of the present invention;
FIG. 12 is a schematic diagram of the block structure of the detecting probe according to the embodiment of the present invention;
fig. 13 is a schematic structural view of a second side window assembly according to an embodiment of the present invention;
fig. 14 is a schematic structural view of a roof window assembly according to an embodiment of the present invention.
Reference numerals: 1, isolating the section; 10 isolating the section frame; 100 mounting holes; 11 side window blocking blocks; 12 a first side window assembly; 120 a first side window platen; 1200 a first horizontal portion; 1201 a first bending section; 121 a first side window support plate; 1210 a second horizontal portion; 1211 a second bending part; 1212 a second extension; 122 a first side window viewing aperture; 13 an injection member; 130 large support plates; 131 small support plates; 132 an injection hole; 133 a fuel channel; 134 a fuel nozzle; 14 plugging a flat plugging block; 2, a windowing combustion section; 20 a combustion chamber frame; 21, a top window block; 22 a second side window assembly; 220 a second side window press plate; 2200 the third horizontal part; 2201 a third bending part; 221 a second side window support plate; 2210 a fourth horizontal portion; 2211 fourth bend; 2212 a fourth extension; 222 a second side window viewing aperture; 23 pressure measuring holes; 24 small ignition location holes; 25 ignition location holes; 26 a cavity stabilization zone; 27 slope; 28 a sleeve; 3, an expansion section; 29 a roof window assembly; 290 a top window press plate; 2900 fifth horizontal part; 2901 a fifth bending part; 291 top window support plate; 2910 a sixth horizontal portion; 2911 a sixth bending part; 2912 a sixth extension; 292 top window inspection holes; 30 expanding the section frame; 31 a detection probe; 32 detecting a probe blockage; 40 a first water component detection module; 41 a second water component detection module; 5, a flange; 6, connecting blocks; 7 supersonic air flow channel; 70 supersonic velocity inlet; 71 a supersonic outlet; 8 quartz glass; 9 asbestos gasket.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the present invention, and not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Example 1
The embodiment 1 of the utility model provides a ground test model for supersonic combustion foundation research, the model includes isolation section 1, windowing combustion section 2, expansion section 3 and water component detection module, be provided with supersonic airflow channel 7 in the model, supersonic airflow channel 7 runs through isolation section 1, windowing combustion section 2 and expansion section 3 in proper order; the isolation section 1 comprises an isolation section frame 10 and a first side surface assembly, the first side surface assembly is arranged on the side surface of the isolation section frame 10, mounting holes 100 are formed in the top and the bottom of the isolation section frame 10, and the isolation assembly is mounted in the mounting holes 100;
the windowing combustion section 2 comprises a combustion chamber frame 20, a second side surface assembly arranged on the side surface of the combustion chamber frame 20 and a top surface assembly arranged on the top of the isolation section frame 10; the dilating segment 3 comprises a dilating segment frame 30;
the water component detection module comprises a first water component detection module 40 and a second water component detection module 41, the first water component detection module 40 is arranged at the front end of the isolation section 1, and the second water component detection module 41 is arranged at the tail end of the expansion section 3;
the front end of the isolation section 1 is connected with a first water component detection module 40 through a flange 5, the rear end of the isolation section 1 is connected with the front end of the windowing combustion section 2 through the flange 5, the rear end of the windowing combustion section 2 is connected with the front end of the expansion section 3 through the flange 5, and the tail end of the expansion section 3 is connected with a second water component detection module 41 through a connecting block 6;
supersonic air flow channel 7 includes supersonic import 70 and supersonic export 71, supersonic import 70 locates the front end of first water component detection module 40, and supersonic export 71 sets up in the end of second water component detection module 41.
The first water component detection module 40 detects the water component (water vapor content) of the high-temperature hot gas flow before combustion, the second water component detection module 41 detects the water component (water vapor content) of the high-temperature hot gas flow after combustion, and the water component conditions of the two are compared to obtain the combustion efficiency.
The first and second water component detecting modules 40 and 4 may employ TDLAS integrated measuring modules.
The first side assembly is a first side window assembly 12, the second side assembly is a second side window assembly 22, and the top assembly is a top window assembly 2221.
The first side window assembly 12 and the second side window assembly 22 are identical in structure;
the first side window assembly 12 includes: a first side window pressing plate 120 and a first side window supporting plate 121, wherein the first side window pressing plate 120 presses on the first side window supporting plate 121.
The first side window pressing plate 120 includes a first horizontal portion 1200 and a first bending portion 1201 connected to the first horizontal portion 1200 in a bending manner; the first side window supporting plate 121 includes a second horizontal portion 1210, a second bending portion 1211 connected to the second horizontal portion 1210 in a bending manner, and a second extending portion 1212 extending toward the inner side of the first side window assembly 12 along the second bending portion 1211; the first bent portion 1201 is in close contact with the second bent portion 1211, and the first horizontal portion 1200 is in close contact with the second horizontal portion 1210.
The bottom of the first side window assembly 12 is provided with a quartz glass 8, and the mouth of the first side window assembly 12 forms a first side window observation hole 122 for observing the mixing process of the fuel.
The first bent portion 1201 is pressed against the upper surface of the quartz glass 8, and the inner side of the second bent portion 1211 is in contact with the quartz glass 8. An asbestos gasket 9 is arranged between the quartz glass 8 and the first bending part 1201, and an asbestos gasket 9 is arranged between the upper surface of the second extending part 1212 and the quartz glass 8 to prevent the quartz glass from being broken. The first side window pressing plate 120 and the first side window supporting plate 121 are made of a metal material.
The second sidelite assembly 22 includes: a second side window pressing plate 220 and a second side window supporting plate 221, wherein the second side window pressing plate 220 presses on the second side window supporting plate 221.
The second side window pressing plate 220 includes a third horizontal portion 2200 and a third bending portion 2201 bent and connected to the third horizontal portion 2200; the second side window supporting plate includes a fourth horizontal portion 2210, a fourth bending portion 2211 connected to the fourth horizontal portion 2210 in a bending manner, and a fourth extending portion 2222 extending toward the inner side of the second side window assembly 22 along the fourth bending portion 2211; the third bent portion 2201 is in close contact with the fourth bent portion 2211, and the third horizontal portion 2200 is in close contact with the fourth horizontal portion 2210.
The bottom of the second side window assembly 22 is provided with a quartz glass 8, and the mouth of the second side window assembly 22 forms a second side window observation hole 222 for observing the combustion flame condition of the windowed combustion section.
The third bending portion 2201 presses the upper surface of the quartz glass 8, and the inner side of the fourth bending portion 2211 contacts the quartz glass 8. An asbestos gasket 9 is disposed between the quartz glass 8 and the third bending portion 2201, and an asbestos gasket 9 is disposed between the upper surface of the fourth extending portion 2212 and the quartz glass 8 to prevent the quartz glass from being broken. The second side window pressing plate 220 and the second side window supporting plate 221 are made of metal.
The top window assembly 29 is used for projecting a laser sheet for particle scattering during fuel tracing, and the scattered light information is received through the second side window assembly, so that a distribution image of the fuel can be obtained. In the embodiment of the present invention, the bottom surface of the roof window assembly 29 is inclined to match the shape of the expansion section, see fig. 14. The embodiment of the utility model provides an in the shape right the utility model discloses a protection scope does not play the limiting action.
The roof window assembly 29 includes: a top window pressing plate 290 and a top window supporting plate 291, wherein the top window pressing plate 290 presses on the top window supporting plate 291.
The top window pressure plate 290 includes a fifth horizontal portion 2900 and a fifth bent portion 2901 bent and connected to the fifth horizontal portion 2900; the top window support plate comprises a sixth horizontal portion 2910, a sixth bent portion 2911 connected with the sixth horizontal portion 2910 in a bent mode, and a sixth extending portion 2929 extending towards the inner side of the top window assembly 29 along the sixth bent portion 2911; the fifth bending portion 2901 is in close contact with the sixth bending portion 2911, and the fifth horizontal portion 2900 is in close contact with the sixth horizontal portion 2910.
The bottom of the top window assembly 29 is provided with quartz glass 8, and the mouth of the top window assembly 29 forms a top window observation hole 292.
The fifth bent portion 2901 is pressed against the upper surface of the silica glass 8, and the inner side of the sixth bent portion 2911 is in contact with the silica glass 8. An asbestos gasket 9 is provided between the silica glass 8 and the fifth bent portion 2901, and an asbestos gasket 9 is provided between the upper surface of the sixth extension portion 2912 and the silica glass 8, so that the silica glass is prevented from being broken. The top window pressure plate 290 and the top window support plate 291 are metallic materials.
Referring to fig. 14, further, the bottom surface of the roof window assembly 14 is disposed at an angle.
The isolation component is an injection member 13, and the injection member 13 is installed in the installation hole 100;
the injection member 13 comprises: the large support plate 130 and the small support plate 131 connected with the large support plate 130, wherein the size and the shape of the small support plate 131 are matched with those of the mounting hole 100; an injection hole 132 is formed in one side, away from the small support plate 131, of the large support plate 130; the small support plate 131 is internally provided with a fuel channel 133, a side of the small support plate 131, which faces away from the large support plate 130, is provided with a fuel nozzle 134, the injection hole 132, the fuel channel 133 and the fuel nozzle 134 are communicated with each other, and the fuel nozzle 134 is communicated with the supersonic air flow channel 7. The injection orifice 132 may be a Ningbo nipple. The injection hole 132 is connected to a fuel reservoir (not shown) which may be kerosene. The fuel passes through the injector holes 132, into the fuel passage 133, and then through the fuel nozzles 134 into the supersonic flow passage 7.
A cavity stable area 26 is formed at the lower part of the combustion chamber frame 20, and a slope 27 is formed at one end of the cavity stable area 26 close to the expanding section 3; the direction of the ramp 27 is gradually increasing in the direction of the flow of the hot gas stream.
The re-entrant stabilisation zone 26 may be windowed through the side of the windowed combustion section 2 to allow observation of the ignition and flame stabilisation process.
The lower end of the bowl stabilizing area 26 defines two ignition-location holes 25, one of which 25 has a sleeve 28 disposed therein to define a small ignition-location hole 24. This embodiment provides one ignition site hole 25 and one small ignition site hole 24 to accommodate different sized spark plugs. When one of the holes is used for installing the spark plug, the other hole is plugged by a plug (not shown in the drawing, the shape of which can be seen in the detection probe plug 32 of fig. 12) matched with the size and the shape of the hole.
Example 2
In embodiment 2 of the present invention, the top surface component is an injection member 13, a cavity is disposed at the top and the side of the combustion chamber frame 20, and the injection member 13 is installed in the cavity;
the isolation component is arranged to be a blocking and flat blocking block 14, the installation hole 100 of the isolation section 1 is blocked by the blocking and flat blocking block 14, and the structural form of the blocking and flat blocking block 14 is shown in fig. 11. The fuel is injected by a top surface assembly which may take the form of the injection member of example 1.
Optionally, an injection member is arranged at the top of the windowing combustion section 2, and the ground of an injection structure of the injection member is arranged to be an inclined surface so as to be matched with the shape of the rear expansion section. Obviously, the shape in the embodiment of the present invention does not limit the protection scope of the present invention.
Alternatively, the first side assembly may be used as a side window block 11. The structure of the side window block 11 is shown with reference to fig. 10. When the windowed view is not needed, the sides of the insulation segment frame 10 are plugged.
The other structures are the same as those of embodiment 1, and are not described herein again.
Example 3
The top surface component is a top window block 21, a pressure measuring hole 23 is arranged on the top window block 21, and the pressure measuring hole 23 is connected with a pressure sensor (not shown in the attached drawing) and used for detecting the pressure condition of the windowing combustion section 2. The pressure taps 23 may be nipples.
Alternatively, the first side assembly may be used as a side window block 11. The structure of the side window block 11 is shown with reference to fig. 10. When the windowed view is not needed, the sides of the insulation segment frame 10 are plugged.
The other structures are the same as those of embodiment 1, and are not described herein again.
Example 4
The top surface component is a top window block 21, a pressure measuring hole 23 is arranged on the top window block 21, and the pressure measuring hole 23 is connected with a pressure sensor (not shown in the attached drawing) and used for detecting the pressure condition of the windowing combustion section 2. The pressure taps 23 may be nipples. Obviously, in the embodiment of the present invention, the bottom surface of the top window block 21 is inclined to match the shape of the rear expansion section. Further, the pressure measuring holes 23 are arranged in an array.
The first side component is a side window block 11. The structure of the side window block 11 is shown with reference to fig. 10. When the windowed view is not needed, the sides of the insulation segment frame 10 are plugged.
The expansion section frame 30 is provided with a detection probe 31, and the speed and temperature of the airflow are detected through the detection probe 31. The detection probe 31 of the present embodiment is a discrete TDLAS measurement probe. Optionally, the detection probe 3 is arranged in an up-down mirror image or in a left-right mirror image. The supersonic flame is formed in the expansion section 3 and can be measured by a discrete TDLAS measuring probe.
When the detection is not needed, the detection probe block 32 can be installed in the detection probe 31 to block the detection probe 31. The inside of the test probe block 32 fits into the test probe 31, see fig. 12. In this embodiment, the detection probes 31 are provided at a plurality of positions of the extension section 3, and a part of the detection probes 31 may be blocked, and the speed and temperature of the two detection probes 31 at the opposite mirror positions may be measured by the speed sensor and the temperature sensor.
The other structures are the same as those of embodiment 1, and are not described herein again.
It should be noted that, in the embodiment of the present invention, the following multiple functions can be implemented:
(1) observing the fuel mixing condition of the isolated section through the first side window assembly 12;
(2) observing the combustion flame condition of the windowed combustion section through the second sidelite assembly 22; when the second sidelite assembly 22 is not in use, it may be plugged with a sidelite plug 11.
(3) Arranging an injection member at the top or the side of the isolation section 1, and injecting fuel at the isolation section 1; when not in use
(4) An injection member is arranged on the side surface or the top of the windowing combustion section 2, and fuel injection is carried out at the windowing combustion section 2; when the top of the windowing combustion section 2 is provided with the injection member, the ground of the injection structure is set to be an inclined surface, so that the injection member is matched with the shape of the rear expansion section.
(5) A top window block 21 is arranged at the top of the windowing combustion section 2, a pressure measuring hole 23 is arranged on the top window block 21, and the pressure of the top window block is detected; or through the top window assembly 29, can be used to project laser sheets for particle scattering during fuel tracking, and through the second side window assembly, receiving the scattered light information, a distribution image of the fuel can be obtained. The roof window block 21 and the roof window assembly 29 may be interchanged.
(6) A detection probe and a detection probe block are arranged at the expansion section, and the detection probe block is detached when detection is needed, so that the speed and the temperature of the detection probe block are detected;
above-mentioned multiple functions can the flexibility combination, realize the utility model discloses the required function of embodiment. One or more functions may be performed simultaneously.
The embodiment of the utility model provides a theory of operation does:
the front end of the model of the embodiment is connected with a heater (not shown in the figure), and high-temperature hot gas heated by the heater flows through a supersonic inlet 70 and enters a supersonic airflow channel 7;
in supersonic velocity airflow channel 7, high temperature air current and fuel carry out the co-combustion, form flame in cavity stable region 26, then export 71 through supersonic velocity and discharge the hot gas flow, this practical embodiment adopts isolation section, windowing burning section, expansion section three-section to detect or observe etc to find the best experimental position, make final finished product spare, avoid frequent preparation experiment model finished product spare.
The foregoing is illustrative of the preferred embodiment of the present invention and is not to be construed as limiting the invention in any way. Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments by the technical entity of the present invention should fall within the protection scope of the technical solution of the present invention.
Claims (10)
1. A ground test model for supersonic combustion foundation research is characterized in that the model comprises an isolation section (1), a windowing combustion section (2), an expansion section (3) and a water component detection module, a supersonic airflow channel (7) is arranged in the model, and the supersonic airflow channel (7) sequentially penetrates through the isolation section (1), the windowing combustion section (2) and the expansion section (3); the isolation section (1) comprises an isolation section frame (10) and a first side surface assembly, the first side surface assembly is arranged on the side surface of the isolation section frame (10), mounting holes (100) are formed in the top and the bottom of the isolation section frame (10), and the isolation assembly is mounted in the mounting holes (100);
the windowing combustion section (2) comprises a combustion chamber frame (20), a second side surface assembly arranged on the side surface of the combustion chamber frame (20) and a top surface assembly arranged at the top of the isolation section frame (10); the expanding section (3) comprises an expanding section frame (30);
the water component detection module comprises a first water component detection module (40) and a second water component detection module (41), the first water component detection module (40) is arranged at the front end of the isolation section (1), and the second water component detection module (41) is arranged at the tail end of the expansion section (3);
the front end of the isolation section (1) is connected with a first water component detection module (40), the rear end of the isolation section (1) is connected with the front end of the windowing combustion section (2), the rear end of the windowing combustion section (2) is connected with the front end of the expansion section (3), and the tail end of the expansion section (3) is connected with a second water component detection module (41);
supersonic speed air current passageway includes supersonic speed import (70) and supersonic speed export (71), first water component detection module (40) front end is located in supersonic speed import (70), and supersonic speed export (71) sets up in the end of second water component detection module (41).
2. A ground test model as claimed in claim 1, wherein the first side assembly is a first side window assembly (12);
the second side assembly is a second side window assembly (22) and the top assembly is a top window assembly (29).
3. A ground test model as claimed in claim 2, wherein the first and second side window assemblies (12, 22) are identical in construction.
4. A ground test model according to claim 1, characterized in that the isolation component is an injection member (13), the injection member (13) being mounted within the mounting hole (100);
the injection member (13) comprises: the large support plate (130) and the small support plate (131) connected with the large support plate (130), wherein the size and the shape of the small support plate (131) are matched with those of the mounting hole (100); an injection hole (132) is formed in one side, away from the small support plate (131), of the large support plate (130); the fuel channel (133) is arranged inside the small support plate (131), the fuel nozzle (134) is arranged on one side, away from the large support plate (130), of the small support plate (131), the injection hole (132), the fuel channel (133) and the fuel nozzle (134) are communicated with one another, and the fuel nozzle (134) is communicated with the supersonic air flow channel (7).
5. A ground test model according to claim 1, characterized in that the ceiling assembly is an injection member (13) provided with cavities at the top and sides of the combustion chamber frame (20), the injection member (13) being mounted in the cavities, the insulation assembly being provided as a block (14).
6. The ground test model as recited in claim 1, characterized in that the top surface component is a top window block (21), a pressure measuring hole (23) is arranged on the top window block (21), and a pressure sensor is connected to the pressure measuring hole (23).
7. The ground test model of claim 1, characterized in that the lower part of the combustion chamber frame (20) forms a cavity stabilization zone (26), and the end of the cavity stabilization zone (26) close to the expansion section (3) is formed with a slope (27); two ignition-location holes (25) are formed in the lower end of the cavity stabilization zone (26), wherein a sleeve (28) is disposed in one of the ignition-location holes (25) to form a small ignition-location hole (24).
8. The ground test model as recited in claim 1, characterized in that the dilating-segment frame (30) is provided with a detecting probe (31).
9. A ground test model according to claim 1, characterized in that the first side component is a side window block (11).
10. A ground test model according to claim 1, characterized in that the insulation component is a block (14).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921303120.3U CN210513708U (en) | 2019-08-13 | 2019-08-13 | Ground test model for supersonic combustion foundation research |
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| CN201921303120.3U CN210513708U (en) | 2019-08-13 | 2019-08-13 | Ground test model for supersonic combustion foundation research |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112664973A (en) * | 2020-12-25 | 2021-04-16 | 中国人民解放军国防科技大学 | Optical observation device for flow direction cross section of flow field in supersonic combustion chamber |
| CN114923696A (en) * | 2022-03-30 | 2022-08-19 | 中国民用航空飞行学院 | Unmanned aerial vehicle micro turbojet engine measurement and control console and measurement and control method |
-
2019
- 2019-08-13 CN CN201921303120.3U patent/CN210513708U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112664973A (en) * | 2020-12-25 | 2021-04-16 | 中国人民解放军国防科技大学 | Optical observation device for flow direction cross section of flow field in supersonic combustion chamber |
| CN112664973B (en) * | 2020-12-25 | 2023-08-11 | 中国人民解放军国防科技大学 | Supersonic combustion chamber flow field flow direction cross section optical observation device |
| CN114923696A (en) * | 2022-03-30 | 2022-08-19 | 中国民用航空飞行学院 | Unmanned aerial vehicle micro turbojet engine measurement and control console and measurement and control method |
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