CN213392904U - High-modulus test supersonic air ejector - Google Patents
High-modulus test supersonic air ejector Download PDFInfo
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- CN213392904U CN213392904U CN202022375970.3U CN202022375970U CN213392904U CN 213392904 U CN213392904 U CN 213392904U CN 202022375970 U CN202022375970 U CN 202022375970U CN 213392904 U CN213392904 U CN 213392904U
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Abstract
The utility model relates to a high modulus test supersonic speed air ejector, including suction nozzle, shrink pipe, hybrid tube and diffusion tube, the suction nozzle the shrink pipe the hybrid tube with the diffusion tube communicates in proper order, wherein, the hybrid tube includes admission valve, discharge valve and hybrid fan, the admission valve is arranged in the inlet end of hybrid tube, discharge valve arranges in the exhaust end of hybrid tube, hybrid fan arranges in discharge valve, just hybrid fan is located the admission valve with between the discharge valve. The shrinkage pipe is utilized to adjust the output ejection gas, the mixing pipe is utilized to fully mix the ejection gas and the ejected gas, the transverse mixing distance of the airflow is reduced, the ejection performance of the air ejector is improved, and the air ejector is suitable for a high-modulus test environment.
Description
Technical Field
The utility model belongs to the technical field of the aviation experimental facilities, concretely relates to experimental supersonic speed air ejector of high mould.
Background
The supersonic air ejector has the vacuumizing function, uses normal-temperature air as a medium, has the advantages of simple structure, small volume, rapid reaction and the like, and is mainly applied to the fields of aerospace, military and national defense, national industry and the like. The existing ejector mode for the conventional hypersonic wind tunnel comprises single-nozzle central ejector, annular ejector, multi-nozzle ejector and the like, and the single-nozzle central ejector is mostly applied to small-caliber ejector occasions due to jet concentration and large noise; the annular ejector is peripheral jet flow, has low noise and low pressure ratio, and is mature in application to small and medium wind tunnels; the multi-nozzle ejector is provided with a mixing chamber, adopts multi-nozzle layout, solves the exhaust pressurization problem of a large-caliber wind tunnel, and is mostly applied to occasions with low pressurization ratio.
The high altitude simulation test (high modulus test for short) is to build a closed cabin body (high altitude cabin) on the ground, place the engine in the cabin body, adjust the cabin pressure to a designed pressure value, then carry out an ignition test, measure the high altitude thrust of the engine, and maintain the cabin pressure constant in the whole process of the engine. The high-modulus test belongs to a performance test and is used for accurately measuring the vacuum specific impulse and the thrust of an engine and checking the structural reliability and the heat transfer characteristic of a large-expansion-ratio spray pipe under a low-pressure condition. The supersonic ejector which is used for carrying out high-modulus test on the ground and has wide application prospect in the high-modulus test has the advantages that a low-pressure vacuum environment under the corresponding height must be established, and the low-pressure airflow is discharged to the environment with higher pressure by using the ejection pressurization effect of the supersonic jet.
The operational environment of the supersonic ejector at the present stage is mostly the ground pressure environment, and the structure of the supersonic ejector is more complicated moreover, and for further expanding the service environment of the supersonic ejector, normal operation of equipment in the high-modulus test environment is the problem that needs to be solved now urgently.
SUMMERY OF THE UTILITY MODEL
In order to solve the above problems existing in the prior art, the utility model provides a high mould test supersonic speed air ejector. The to-be-solved technical problem of the utility model is realized through following technical scheme:
a supersonic air ejector for high modulus tests comprises an air inlet nozzle, a contraction pipe, a mixing pipe and a diffusion pipe, wherein the air inlet nozzle, the contraction pipe, the mixing pipe and the diffusion pipe are sequentially connected through bolts,
the hybrid tube includes admission valve, discharge valve, hybrid fan and hybrid tube body, the admission valve is arranged in the inlet end of hybrid tube body, discharge valve arranges in the exhaust end of hybrid tube body, hybrid fan arranges in the hybrid tube body, just hybrid fan is located the admission valve with between the discharge valve.
In one embodiment of the invention, the convergent tube comprises a first nozzle, a second nozzle and a convergent tube body, the first nozzle being comprised of a first equal segment and a first convergent segment, the second nozzle being comprised of a second equal segment and a second convergent segment, wherein,
the first nozzle is connected to one side of the pipe wall of the inlet end of the shrinkage pipe body, the first reducing section of the first nozzle is arranged in the pipe wall of the shrinkage pipe body, and the first equivalent section of the first nozzle is arranged outside the pipe wall of the shrinkage pipe body;
the second nozzle is connected to the other side of the pipe wall of the inlet end of the shrinkage pipe body, the second nozzle and the first nozzle are symmetrical about the center of the shrinkage pipe body, the second reducing section of the second nozzle is arranged in the pipe wall of the shrinkage pipe body, and the second equal-value section of the second nozzle is arranged outside the pipe wall of the shrinkage pipe body.
In one embodiment of the present invention, the first nozzle and the second nozzle are both laval nozzles.
In an embodiment of the present invention, the contraction tube is composed of a contraction straight tube section and a contraction tapered section, and the reduction angle is 5 ° to 10 °.
In one embodiment of the present invention, the air intake valve is a piston type air intake valve.
In an embodiment of the present invention, the exhaust valve is a piston exhaust valve.
The utility model has the advantages that:
the application provides a high modulus experimental supersonic speed air ejector, including suction nozzle, shrink pipe, hybrid tube and diffuser tube, the suction nozzle the shrink pipe the hybrid tube with the diffuser tube connects gradually through the bolt, is drawn gaseous from the suction nozzle and gets into this air ejector, mixes through shrink pipe and drawing gaseous in the hybrid tube, and by the diffuser tube blowout at last, utilize the shrink pipe can adjust the ejection gas of drawing of output, utilize the hybrid tube can be to drawing penetrate gaseous and by drawing the ejection gas and carry out intensive mixing, reduced the horizontal mixing distance of air current, improved the ejection performance of this air ejector, make this air ejector adapt to high modulus experimental environment.
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Drawings
Fig. 1 is a schematic structural diagram of a supersonic air ejector for high-modulus test provided by an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a first nozzle and a second nozzle provided by an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a shrink tube according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a diffusion tube according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific examples, but the present invention is not limited thereto.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic structural diagram of a supersonic air ejector for high modulus test provided by an embodiment of the present invention, and fig. 2 is a schematic structural diagram of a first nozzle and a second nozzle provided by an embodiment of the present invention. The embodiment of the utility model provides a high modulus test supersonic air ejector, which comprises an air inlet nozzle 1, a contraction pipe 2, a mixing pipe 3 and a diffusion pipe 4, wherein the air inlet nozzle 1, the contraction pipe 2, the mixing pipe 3 and the diffusion pipe 4 are connected in sequence through bolts, wherein,
the air inlet nozzle 1 is used for sucking injected gas;
the contraction pipe 2 is used for sucking or sucking the injection gas, preliminarily mixing the injected gas and the injection gas, and converting the pressure potential energy of the injected gas and the injection gas into kinetic energy;
the mixing pipe 3 is used for mixing the injection gas and the injected gas in the mixing pipe 3 to obtain mixed gas;
and the diffusion pipe 4 is used for converting the kinetic energy of the mixed gas output by the mixing pipe 3 into pressure potential energy and outputting the mixed gas.
Specifically, the air inlet nozzle 1 is connected with an inner cavity of engine fuel, air generated by the engine is injected air, the injected air enters the air ejector from the air inlet nozzle 1, enters the mixing pipe 3 through the contraction pipe 2, and is finally discharged out of the air ejector through the diffusion pipe 4.
Further, the convergent tube 2 comprises a first nozzle 21, a second nozzle 22 and a convergent tube body 23, the first nozzle 21 consisting of a first equal section 211 and a first convergent section 212, the second nozzle 22 consisting of a second equal section 221 and a second convergent section 222, wherein,
the first nozzle 21 is connected to one side of the tube wall of the inlet end of the shrinkage tube body 23, the first tapered section 212 of the first nozzle 21 is arranged in the tube wall of the shrinkage tube body 23, and the first equivalent section 211 of the first nozzle 21 is arranged outside the tube wall of the shrinkage tube body 23;
the second nozzle 22 is connected to the other side of the pipe wall of the inlet end of the convergent pipe body 23, the second nozzle 22 and the first nozzle 21 are symmetrical about the center of the convergent pipe body 23, the second tapered section 222 of the second nozzle 22 is arranged in the pipe wall of the convergent pipe body 23, and the second equal section 221 of the second nozzle 22 is arranged outside the pipe wall of the convergent pipe body 23.
Specifically, the shrink tube body 23 is provided with a first nozzle 21 and a second nozzle 22, and the first nozzle 21 and the second nozzle 22 are symmetrical with respect to the center of the shrink tube body 23. First nozzle 21 and second nozzle 22 are connected high-pressure gas source, and its gas that lets in is for drawing penetrating gas, and highly compressed draws penetrates gas and turns into kinetic energy with pressure potential energy in shrink tube 2, forms the negative pressure zone in the shrink tube body 23 to carry out the evacuation to the engine inner chamber, for avoiding blind chamber this moment, first nozzle 21 and second nozzle 22 can outwards export simultaneously and draw penetrating gas, reduce pressure loss.
The first nozzle 21 and the second nozzle 22 are both Laval nozzles, the inner molded surface of the Laval nozzle is a curved surface, and the external dimension of the Laval nozzle is consistent with the dimension of a mounting hole of a straight pipe section of the shrinkable pipe 2. The first reducing section 212 of the first nozzle 21 and the second reducing section 222 of the second nozzle 22 both form a certain angle with the straight pipe section of the contraction pipe 2, the angle ranges from 0 degree to 45 degrees, the flow of air flow can be accelerated by 30 degrees in the embodiment, and the injection efficiency of the injector is improved.
Further, please refer to fig. 3, fig. 3 is a schematic structural diagram of the shrinkage pipe provided by the embodiment of the present invention, and the shrinkage pipe body 23 is composed of a shrinkage straight pipe section 25 and a shrinkage tapered section 24, and the shrinkage reduction angle is 5 ° to 10 °.
Specifically, the shrinkage pipe body 23 is composed of a shrinkage straight pipe section 25 and a shrinkage tapered section 24, and can reduce and expand the air flow, convert the pressure potential energy of injected air and injected air into kinetic energy, and prevent the pressure loss caused by air flow dispersion, wherein the shrinkage angle of the shrinkage pipe body 23 is 5 degrees in this embodiment.
Further, the mixing pipe 3 includes an intake valve 31, an exhaust valve 32, a mixing fan 33, and a mixing pipe body 34, the intake valve 31 is disposed at an intake end of the mixing pipe body 34, the exhaust valve 32 is disposed at an exhaust end of the mixing pipe body 34, the mixing fan 33 is disposed in the exhaust valve 32, and the mixing fan 33 is located between the intake valve 31 and the exhaust valve 32.
The inlet valve 31 is a piston type inlet valve.
The exhaust valve 32 is a piston type exhaust valve.
The piston type exhaust valve used in the embodiment is used for adjusting the gas pressure in the mixing pipe, has high sensitivity, can realize quick air inlet and air outlet, and can be of a KKP-20 type for example.
Specifically, the air inlet valve 31 is used for adjusting the volume of the gas input into the mixing pipe 3, the air outlet valve 32 is used for adjusting the volume of the gas output from the mixing pipe 3, and the gas pressure in the mixing pipe 3 can be controlled by the matching adjustment of the air inlet valve 31 and the air outlet valve 32, for example, the air inlet of the air inlet valve 31 is adjusted to be larger, the air outlet of the air outlet valve 32 is adjusted to be smaller, and the gas pressure in the mixing pipe 3 is increased; the air inlet valve 31 is adjusted to be small and the air outlet valve 32 is adjusted to be large to be air outlet, and the air pressure in the mixing pipe 3 is reduced. The center of the mixing fan 33 is arranged on the central shaft of the mixing pipe and is used for fully mixing the injected gas and the injected gas which are input into the mixing pipe 3, so that the contact area of the injected gas flow and the injected gas flow is increased, and the transverse mixing distance of the gas is reduced.
Specifically, the mixing pipe 3 is used for fully and uniformly mixing the preliminarily mixed injected gas and the injected gas, and the pressure and the speed of the mixed fluid are gradually stabilized.
Referring to fig. 4, fig. 4 is a schematic structural diagram of the diffuser according to an embodiment of the present invention, the diffuser 4 is composed of a diffusion divergent section 41 and a diffusion equivalent section 42, the cross section of the diffusion divergent section 41 of the diffuser 4 is gradually increased from the air inlet to the air outlet, and the cross section of the diffusion equivalent section 42 of the diffuser 4 is equal from the air inlet to the air outlet. The diffusion pipe 4 can expand and accelerate the mixed injected gas and the injected gas, and the kinetic energy of the injected gas and the injected gas is converted into pressure potential energy.
To sum up, inject gaseous from the inlet nozzle 1 input by drawing, get into the hybrid tube through shrink tube 2, be provided with first nozzle 21 and second nozzle 22 on the shrink tube body 23 wall, when being penetrated gaseous by drawing and inhale fast, form low pressure vacuum environment in the shrink tube 2, for avoiding forming the blind cavity in the shrink tube 2, utilize first nozzle 21 and second nozzle 22 to draw this air ejector of gaseous output of drawing, increased and penetrated gaseous area of contact with drawing of drawing, the horizontal mixing distance of air current has been reduced, the length of drawing the system of penetrating has been reduced, the feasibility scheme is provided for the high-modulus experimental environment. At the same time. In addition, an air inlet valve 31 is installed at an air inlet of the mixing pipe 3, the volume of input air is adjusted, an exhaust valve 32 is installed at an exhaust port of the mixing pipe 3, the volume of exhaust air is adjusted, and a mixing fan 33 is installed in the mixing pipe 3 and used for fully mixing injected air and injected air which are input into the mixing pipe 3 to obtain mixed air, so that the contact area of injected air flow and injected air flow is further increased, and the transverse mixing distance of air is reduced. Finally, the mixed gas is discharged from the diffuser pipe 4. Utilize shrink pipe 2 can adjust the ejection gas of output, utilize mixing tube 3 can to draw ejection gas and be drawn ejection gas and carry out intensive mixing, reduced the horizontal mixing distance of air current, improved this air ejector's ejection performance, make this air ejector be adapted to high mould test environment.
It will be apparent to those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention; thus, if such modifications and variations of the present invention fall within the scope of the claims and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (6)
1. The supersonic air ejector for the high modulus test is characterized by comprising an air inlet nozzle (1), a contraction pipe (2), a mixing pipe (3) and a diffusion pipe (4), wherein the air inlet nozzle (1), the contraction pipe (2), the mixing pipe (3) and the diffusion pipe (4) are communicated in sequence,
mixing pipe (3) are including admission valve (31), discharge valve (32), hybrid fan (33) and mixing pipe body (34), admission valve (31) are arranged in the inlet end of mixing pipe body (34), discharge valve (32) are arranged in the exhaust end of mixing pipe body (34), hybrid fan (33) are arranged in mixing pipe body (34), just hybrid fan (33) are located admission valve (31) with between discharge valve (32).
2. The high modulus test supersonic air ejector according to claim 1, characterized in that the shrink tube (2) comprises a first nozzle (21), a second nozzle (22) and a shrink tube body (23), the first nozzle (21) consisting of a first equal section (211) and a first tapered section (212), the second nozzle (22) consisting of a second equal section (221) and a second tapered section (222), wherein,
the first nozzle (21) is connected to one side of the pipe wall of the inlet end of the shrinkage pipe body (23), the first tapered section (212) of the first nozzle (21) is arranged in the pipe wall of the shrinkage pipe body (23), and the first equal-value section (211) of the first nozzle (21) is arranged outside the pipe wall of the shrinkage pipe body (23);
the second nozzle (22) is connected to the other side of the pipe wall of the inlet end of the shrinkage pipe body (23), the second nozzle (22) and the first nozzle (21) are symmetrical about the center of the shrinkage pipe body (23), the second tapered section (222) of the second nozzle (22) is placed in the pipe wall of the shrinkage pipe body (23), and the second equal section (221) of the second nozzle (22) is placed outside the pipe wall of the shrinkage pipe body (23).
3. The high mode test supersonic air ejector of claim 2, wherein the first nozzle (21) and the second nozzle (22) are both laval nozzles.
4. The supersonic air ejector for high modulus test according to claim 2, wherein the convergent tube body (23) is composed of a convergent straight tube section (25) and a convergent tapered section (24), and the reduction angle is 5 ° to 10 °.
5. The high mode test supersonic air ejector of claim 1, wherein the air intake valve (31) is a piston type air intake valve.
6. The high mode test supersonic air ejector of claim 1, wherein the vent valve (32) is a piston-type vent valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022375970.3U CN213392904U (en) | 2020-10-22 | 2020-10-22 | High-modulus test supersonic air ejector |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022375970.3U CN213392904U (en) | 2020-10-22 | 2020-10-22 | High-modulus test supersonic air ejector |
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| CN213392904U true CN213392904U (en) | 2021-06-08 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113357007A (en) * | 2021-06-23 | 2021-09-07 | 中国航发沈阳发动机研究所 | Injection discharge device |
| CN113432879A (en) * | 2021-06-23 | 2021-09-24 | 中国航发沈阳发动机研究所 | Injection device |
| CN117928959A (en) * | 2024-03-25 | 2024-04-26 | 中国航空工业集团公司沈阳空气动力研究所 | Ejector type power simulation system of aero-engine icing test bed |
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2020
- 2020-10-22 CN CN202022375970.3U patent/CN213392904U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113357007A (en) * | 2021-06-23 | 2021-09-07 | 中国航发沈阳发动机研究所 | Injection discharge device |
| CN113432879A (en) * | 2021-06-23 | 2021-09-24 | 中国航发沈阳发动机研究所 | Injection device |
| CN113357007B (en) * | 2021-06-23 | 2022-08-19 | 中国航发沈阳发动机研究所 | Injection discharge device |
| CN117928959A (en) * | 2024-03-25 | 2024-04-26 | 中国航空工业集团公司沈阳空气动力研究所 | Ejector type power simulation system of aero-engine icing test bed |
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