CN113958540A - Supersonic air injection device - Google Patents
Supersonic air injection device Download PDFInfo
- Publication number
- CN113958540A CN113958540A CN202111221190.6A CN202111221190A CN113958540A CN 113958540 A CN113958540 A CN 113958540A CN 202111221190 A CN202111221190 A CN 202111221190A CN 113958540 A CN113958540 A CN 113958540A
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- Prior art keywords
- air
- pipe
- air duct
- transition section
- ejector
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/14—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid
- F04F5/16—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
- F04F5/46—Arrangements of nozzles
- F04F5/466—Arrangements of nozzles with a plurality of nozzles arranged in parallel
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention discloses a supersonic air injection device which mainly comprises a mounting plate, an air duct transition section, an injection pipe, a spray pipe, a secondary cooling air duct, a support plate and an inlet pipe nozzle, wherein the injection pipe is arranged in the air duct transition section in the middle, and the spray pipe is a Laval spray pipe which is symmetrically arranged. High-temperature and high-pressure gas enters through the inlet nozzle, flows through the ejector pipe, is ejected from the spray pipe to form a negative pressure area, and low-temperature air is sucked from the air inlet, is mixed at the secondary cooling air duct through the mounting plate and the air duct transition section, and flows out from the air outlet. The invention is used for ejecting low-temperature air by using high-temperature and high-pressure gas, and the ejected low-temperature air can be used as a cold source for supplying equipment for heat dissipation. The invention has more reasonable arrangement of the spray pipe and the flow passage, improves the mixing uniformity of the injection airflow and the injected airflow, and can effectively improve the injection effect.
Description
Technical Field
The invention relates to a supersonic air injection device, and belongs to the field of injector structural design.
Background
When an airplane is on the ground, when low-temperature environment air needs to be pumped to serve as a cold source to dissipate heat of equipment, an ejector is often needed. The length of an air outlet section of an ejector on the airplane is short due to the limitation of an installation space, so that air flows cannot be well mixed; and when the ejector is provided with a plurality of spray pipes, the influence of the Bernoulli effect on the multi-strand jet flow and the wall surface of the flow channel is easy to influence, the mixing of the air flow is further influenced, and the ejection effect is finally influenced.
An air ejector (CN110529438A, 2019-12-03) in the prior patent discloses a structure of an air ejector, but the air ejector is not suitable for the occasions with high space occupation requirements (i.e. the ejector is required to have a very small volume and the ejector has regular appearance requirements), on one hand, the ejector is affected by bernoulli effect, the ejector is still insufficient in the mixing uniformity of the ejector airflow and the ejected airflow, on the other hand, the unique C-shaped ejector pipe structure and the distribution mode of the nozzle easily generate large airflow disturbance, wherein the external mode of the ejector passively reduces the mixing area of the ejector airflow and the ejected airflow, which causes uneven airflow mixing, in addition, the ejector airflow velocity is increased due to asymmetry of the ejector pipe, which causes serious airflow disturbance, and a welding seam exists between the ejector pipe and the air duct shell, the welding seam is irregular and has higher processing requirement.
Disclosure of Invention
The invention aims to provide a supersonic air injection device, which overcomes the defects of the injection device in the prior art, has good injection effect, reduces the disturbance of air flow, adapts to the compact layout of space on an airplane, and greatly improves the injection effect of the air flow in the limited installation space.
In order to achieve the purpose, the invention adopts the following technical scheme:
a supersonic air ejector comprises a mounting plate, an air duct transition section, an ejector pipe, a spray pipe, a secondary cooling air duct and a support plate;
the air channel transition section is a variable cross-section shell which is closed in the circumferential direction and is open at two ends, and one end of the air channel transition section is connected with the mounting plate to form a transition channel with a gradually widened cross section from the air inflow direction to the air outflow direction;
the injection pipe is in a closed ring shape and is arranged in the air channel transition section, a gap is formed between the injection pipe and the inner wall of the air channel transition section, a connecting hole is formed in the surface of the injection pipe, the injection pipe is connected with an inlet pipeline, and the inlet pipeline is connected with a high-temperature high-pressure air source;
the spray pipes are uniformly distributed along the annular peripheral surface of the ejector pipe, and the airflow inlet ends of the spray pipes are communicated with the connecting holes in the ejector pipe;
the secondary cooling air duct is connected with the tail end of the air outflow direction of the air duct transition section, and the secondary cooling air duct is a straight pipeline with a uniform cross section;
the backup pad is located inside the wind channel changeover portion, and will draw and penetrate the pipe and be connected with the wind channel changeover portion.
Alternatively, a positioning hole is formed in the side face of the air duct transition section, and the inlet pipeline penetrates through the positioning hole to be connected with the injection pipe.
Alternatively, the inner surface of the air duct transition section is provided with a plurality of positioning grooves, one end of the supporting plate is arranged in the positioning grooves, and the other end of the supporting plate is connected with the annular peripheral surface of the injection pipe.
Alternatively, the ejector tube is connected to the inlet nozzle via an inlet conduit.
Optionally, the annular central axis of the ejector pipe is parallel to the air flow direction and coincides with the center of the section of the air outlet end of the air duct transition section, so that the annular surface of the ejector pipe is located in the middle of the section of the air outlet end of the air duct transition section.
Alternatively, the circumferential profile of the injection pipe is in a waist-shaped hole shape, a plurality of connecting holes are distributed at equal intervals along the contour line of the waist-shaped hole shape, at least one connecting hole is formed in two arc sections of the contour of the waist-shaped hole, and the connecting holes are all located on the annular surface of the injection pipe, which points to the air outflow end.
As an option, the spray pipe is a Laval spray pipe and is connected with a connecting hole in the injection pipe through a positioning structure.
Alternatively, the direction of the airflow of the spray pipe is consistent with the direction of the airflow in the secondary cooling air channel.
Alternatively, the nozzle has an air flow inlet end angle that is greater than an air flow outlet end angle.
Alternatively, the mounting plate, the air duct transition section, the ejector tube, the spray pipe, the secondary cooling air duct, the support plate and the inlet nozzle are connected in a welding mode.
In the invention, high-temperature and high-pressure gas enters through the inlet nozzle, flows through the ejector pipe, is ejected from the spray pipe to form a negative pressure area, and low-temperature air is sucked from the air inlet, passes through the mounting plate and the air duct transition section, is mixed at the two cold air ducts, and flows out from the air outlet.
The invention is used for ejecting low-temperature air by using high-temperature and high-pressure gas, and the ejected low-temperature air can be used as a cold source for supplying the air to equipment on an airplane for heat dissipation. In consideration of the fact that the number of system equipment on an airplane is large, pipelines are complex, space is limited, and the structural compactness of the injection device needs to be improved, the air injection device is used as an injection cold source of the heat dissipation device and is connected with a cold source outlet of the heat dissipation device through the mounting plate, the inlet nozzle and the secondary cooling air duct are connected with the system pipelines on the airplane, and the annular injection pipe is arranged in the air duct transition section in a built-in mode, so that the structural compactness of the injection device is improved, and the air injection device is suitable for the narrow pipeline space layout on the airplane.
Through careful calculation and verification, the types (Laval nozzles) and sizes of the nozzles, the relative positions (space equal interval symmetrical arrangement) between the nozzles and the flow channel layout (air channel transition section characteristics and secondary cooling air channels) of the nozzles can reduce the influence of Bernoulli effect between jet flows, better uniformly mix the jet flow and the injected flow, effectively improve the jet effect and be shown in the following aspects:
firstly, the ejector pipe adopts an annular design, so that the spray pipes are distributed in a space symmetrical mode, the Bernoulli effect is reduced, the mutual attraction degree of the spray flows of the spray pipes is reduced, the uniform mixing degree of the ejector fluid and the ejected fluid is improved, and the problem of airflow disturbance is correspondingly reduced;
secondly, the ejector pipe is arranged in the air duct transition section, a gap is formed between the ejector pipe and the inner wall of the air duct transition section, two mixed channels of the ejector airflow and the ejected airflow are formed, one channel is an inner ring area of the annular ejector pipe, the other channel is a gap between an outer ring of the annular ejector pipe and the inner wall of the air duct transition section, a secondary cooling air duct is connected to the outlet end of the air duct transition section, the air duct transition section is designed into a mode that the cross section is changed from small to large, the mixed air duct area of the ejector fluid and the ejected fluid is increased (the ejector airflow ejection speed is increased by matching with a Laval nozzle, the area of a negative pressure area is enlarged, the air duct mixing area is enlarged), and the disturbance of the airflow is reduced;
and thirdly, the structural form of the laval nozzle is selected for the nozzle, so that the jet speed of the airflow is improved, and the jet effect is improved. The front half part of the Laval nozzle is of a structure with a large-section small section and contracted to the throat pipe towards the middle, the throat pipe is changed from a small section to a large section to expand outwards, high-pressure gas flows into the front half part of the nozzle pipe and passes through the throat pipe to be sprayed out from the rear half part, the nozzle design enables the speed of the gas flow to change due to the change of the section area, the flow speed of the gas flow is enabled to be changed from subsonic speed to sonic speed until the speed is accelerated to supersonic speed, the spraying of supersonic fluid generates huge thrust, the negative pressure area is enlarged, and the negative pressure is increased, so that the injection effect is greatly improved in a limited space;
fourthly, the spray pipes are arranged symmetrically at equal intervals in space and are positioned in the middle of the air duct transition section and the secondary cooling air duct, and the distribution mode prevents the mutual attraction between the jet flows of the adjacent spray pipes, so that the spatial uniformity of the jet flow is improved;
fifthly, the ejector pipe is arranged in the middle of the air channel (the section of the airflow outlet is centered), the ejector pipe is annular, and the shapes of the sections of the air channel (the air channel transition section and the secondary cooling air channel) are both annular structures as the spatial layout of the ejector pipe, so that the jet flow and the wall surface of the air channel are not easily influenced by the Bernoulli effect; on the other hand, the area of the mixed air channel of the injection fluid and the injected fluid is increased by adopting the variable-section air channel transition section from small to large, and the problem that the jet flow and the wall surface of the air channel are easily influenced by the Bernoulli effect is also reduced;
sixthly, the mode that the air duct transition section is connected with the ejector pipe through the supporting plate reduces the processing difficulty, avoids the occurrence of irregular welding seams and improves the working reliability of the ejector device.
Drawings
FIG. 1 is a schematic view of the installation structure of the supersonic ejector according to the present invention;
FIG. 2 is a left side view of FIG. 1;
FIG. 3 is a schematic view of the mounting plate structure of the present invention;
FIG. 4 is a schematic view of a transition section of the air duct of the present invention;
FIG. 5 is a schematic drawing of an eductor tube configuration of the present invention;
FIG. 6 is a schematic view of the nozzle configuration of the present invention;
FIG. 7 is a schematic structural view of a secondary cooling air duct according to the present invention;
FIG. 8 is a schematic view of the structure of the support plate of the present invention;
FIG. 9 is a schematic view of an inlet nozzle configuration of the present invention;
in the figure: the air-conditioning system comprises a mounting plate 1, an air duct transition section 2, an injection pipe 3, a spray pipe 4, a cooling air duct 5, a support plate 6 and an inlet nozzle 7.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
As shown in fig. 1 to 9, in this embodiment, the supersonic air ejector includes a mounting plate 1, an air duct transition section 2, an ejector pipe 3, a nozzle 4, a secondary cooling air duct 5, a support plate 6, and an inlet nozzle 7. All components of the injection device are connected together by welding; the mounting plate 1, the air duct transition section 2 and the secondary cooling air duct 5 shown in fig. 3, 4 and 7 are connected into a whole air duct by welding; the injection pipe 3, the spray pipe 4 and the inlet nozzle 7 shown in fig. 5, 6 and 9 are assembled together and welded into a whole, and the assembling positions of the injection pipe 3, the spray pipe 4 and the inlet nozzle 7 comprise positioning structures; the air duct transition section 2 and the injection pipe 3 shown in fig. 4 and 5 are welded together through a positioning hole and an inlet pipeline; the air duct transition section 2, the injection pipe 3 and the support plate 6 shown in fig. 4, 5 and 8 are welded together through positioning grooves.
As shown in fig. 1, the annular ejector pipe 3 is located in the middle of the cross section of the air duct transition section 2, and the annular area of the ejector pipe 3 is smaller than the cross section area of the air duct transition section 2, so that the air duct is divided into an inner annular passage of the ejector pipe 3 and an outer annular passage between the ejector pipe 3 and the inner wall of the air duct transition section 2.
As shown in fig. 3, the mounting plate 1 is a flange-shaped flat plate, an air inlet window is formed in the middle of the mounting plate, and the injection device is mounted on the equipment through the mounting plate 1 and introduces low-temperature air.
As shown in fig. 4, the air duct transition section 2 is a circumferential closed housing with a gradually widened cross section, and forms a variable cross section passage for air to flow in and out, ambient air to be injected enters the injection device through an air inlet (indicated by a left arrow in fig. 2), and the air duct transition section 2 is provided with 1 positioning hole for fixing the injection pipe 3 and the inlet pipeline. The variable cross-section characteristic of the air duct transition section 2 increases the mixing area of the injection air flow and the injected air flow, reduces air flow disturbance, and the injection air flow and the injected air flow are mixed in a closed space formed by the air duct transition section 2 and the secondary cooling air duct 5 and are not influenced by the air flow disturbance of the external environment.
As shown in fig. 5, the ejector pipe 3 is a circular pipe with a waist-shaped hole, and the outer circumferential surface of the airflow outlet is provided with connecting holes for connecting with the nozzle 4, and fig. 5 shows 14 connecting holes, which are located on a plane and distributed on the contour line of the waist-shaped hole at equal intervals, wherein 1 connecting hole is respectively arranged in the middle of two circular arc sections of the contour line of the waist-shaped hole. The injection pipe 3 is assembled with the spray pipe 4 through a connecting hole and is welded and sealed. The injection pipe 3 is positioned in the air duct transition section 2, the normal line of the plane where the 14 connecting holes are positioned is parallel to the air flowing direction of the injection device, and the midpoint of the waist-shaped hole-shaped contour line where the 14 connecting holes are positioned (namely, the midpoint of the injection pipe 3 in fig. 1 is coincided with the middle position of the cross section of the air outlet end of the air duct transition section 2, so that the injection pipe 3 in fig. 1 is just positioned at the middle position of the air duct transition section 2 and the secondary cooling air duct 5).
As shown in fig. 1 and 5, the spatial distribution of the 14 nozzles 4 is symmetrical, and the flow field generated by the symmetrical distribution is more uniform and the injection effect is better.
As shown in fig. 6, the nozzle 4 is a laval nozzle having an inlet end with an angle a greater than an outlet end with an angle b.
As shown in fig. 6, the nozzle 4 is a laval nozzle, and the angle of the gas flow inlet end of the nozzle 4 is greater than the angle of the gas flow outlet end. The spray pipe 4 comprises a positioning structure, namely a U-shaped structure (a U-shaped surface in an oval area A in fig. 6) at the connecting surface, and the U-shaped surface of the spray pipe 4 is assembled with the connecting hole in the outer circumferential surface of the ejector pipe 3 and is welded and sealed, so that the air leakage probability of the ejector pipe 3 is reduced, the stability of the airflow in the area of the ejector pipe 3 is ensured, and the occurrence of large-amplitude airflow disturbance is avoided. The Laval nozzle can greatly improve the speed of the jet airflow outlet to supersonic speed, thereby improving the injection effect.
As shown in fig. 7, the secondary cooling air duct 5 is a straight duct with a uniform cross section, and is connected to the air outlet end of the air duct transition section 2, so as to achieve the purpose of fully mixing the high-temperature high-pressure gas and the injected low-temperature air.
As shown in fig. 4 and 8, the 6 supporting plates 6 connect the air duct transition section 2 and the injection pipe 3 into a whole through 6 positioning slots on the air duct transition section 2.
As shown in fig. 9, the inlet nozzle 7 is mounted on the apparatus, and high-temperature and high-pressure air is introduced.
According to the invention, the ejector pipe 3 is an annular circular section pipe, the spray pipes 4 are symmetrically distributed on the airflow outflow section of the ejector pipe 3 at equal intervals, the air channel area for mixing the ejector fluid and the ejected fluid is increased, the whole air channel is a regular and approximately symmetrical annular straight air channel (formed by combining the air channel transition section 2 and the secondary cooling air channel 5), and the structural design is beneficial to reducing turbulence and improving the airflow mixing effect. The mode that draws 3 inbuilt compares external mode and has reduced the disturbance influence of external environment air current on the one hand under the condition that the same space occupy, on the other hand has increased and has drawn the mixed cross-sectional area who penetrates the air current and be drawn the air current.
The above embodiments are not intended to limit the scope of the present invention, and any variations, modifications, or equivalent substitutions made on the technical solutions of the present invention should fall within the scope of the present invention.
Claims (10)
1. The utility model provides a supersonic speed air induction system which characterized in that: comprises a mounting plate (1), an air duct transition section (2), an ejector pipe (3), a spray pipe (4), a secondary cooling air duct (5) and a support plate (6);
the air channel transition section (2) is a variable cross-section shell which is closed in the circumferential direction and is open at two ends, one end of the air channel transition section (2) is connected with the mounting plate (1) to form a transition channel with a gradually widened cross section from the air inflow direction to the air outflow direction;
the injection pipe (3) is in a closed ring shape and is arranged inside the air channel transition section (2), a gap is formed between the injection pipe (3) and the inner wall of the air channel transition section (2), a connecting hole is formed in the surface of the injection pipe (3), the injection pipe (3) is connected with an inlet pipeline, and the inlet pipeline is connected with a high-temperature high-pressure air source;
the spray pipes (4) are uniformly distributed along the annular peripheral surface of the ejector pipe (3), and the airflow inlet ends of the spray pipes (4) are communicated with the connecting holes in the ejector pipe (3);
the secondary cooling air duct (5) is connected with the tail end of the air outflow direction of the air duct transition section (2), and the secondary cooling air duct (5) is a straight pipeline with a uniform cross section;
the support plate (6) is located inside the air duct transition section (2) and is connected with the injection pipe (3) and the air duct transition section (2).
2. The supersonic air ejector of claim 1, wherein: the side surface of the air duct transition section (2) is provided with a positioning hole, and an inlet pipeline penetrates through the positioning hole to be connected with the injection pipe (3).
3. The supersonic air ejector of claim 1, wherein: the air duct transition section (2) is provided with a plurality of locating grooves on the inner surface, one end of the supporting plate (6) is arranged in the locating grooves, and the other end of the supporting plate (6) is connected with the annular outer peripheral surface of the injection pipe (3).
4. The supersonic air ejector of claim 1, wherein: the injection pipe (3) is connected with the inlet nozzle (7) through an inlet pipeline.
5. The supersonic air ejector of claim 1, wherein: the annular central axis of the injection pipe (3) is parallel to the air flowing direction and coincides with the center of the section of the air outflow end of the air duct transition section (2), so that the annular surface of the injection pipe (3) is positioned in the middle of the section of the air outflow end of the air duct transition section (2).
6. The supersonic air ejector of claim 1, wherein: the circumferential profile of the injection pipe (3) is in a waist-shaped hole shape, a plurality of connecting holes are distributed at equal intervals along the contour line of the waist-shaped hole shape, at least one connecting hole is formed in two arc sections of the contour of the waist-shaped hole, and the connecting holes are all located on the annular surface of the injection pipe (3) pointing to the air outflow end.
7. The supersonic air ejector of claim 1, wherein: the spray pipe (4) is a Laval spray pipe and is connected with the connecting hole on the injection pipe (3) through a positioning structure.
8. The supersonic air ejector of claim 1, wherein: and the direction of the air flow of the spray pipe (4) is consistent with the direction of the air flow in the secondary cooling air duct (5).
9. The supersonic air ejector of claim 1, wherein: the angle of the airflow inlet end of the spray pipe (4) is larger than that of the airflow outlet end.
10. The supersonic air ejector of claim 1, wherein: the mounting plate (1), the air duct transition section (2), the ejector pipe (3), the spray pipe (4), the secondary cooling air duct (5), the support plate (6) and the inlet nozzle (7) are connected in a welding mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111221190.6A CN113958540B (en) | 2021-10-20 | 2021-10-20 | Supersonic air injection device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111221190.6A CN113958540B (en) | 2021-10-20 | 2021-10-20 | Supersonic air injection device |
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| Publication Number | Publication Date |
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| CN113958540A true CN113958540A (en) | 2022-01-21 |
| CN113958540B CN113958540B (en) | 2023-06-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111221190.6A Active CN113958540B (en) | 2021-10-20 | 2021-10-20 | Supersonic air injection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116571371A (en) * | 2023-07-06 | 2023-08-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Ejector device combining distributed two-dimensional spray pipe and traditional circumferential seam |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190010962A1 (en) * | 2017-07-06 | 2019-01-10 | Altevac Llc | High efficiency aspirator for inflatable emergency slides |
| CN208619425U (en) * | 2018-06-15 | 2019-03-19 | 北京航空航天大学 | Bleed ring, injector and injection inflation system |
| CN110529438A (en) * | 2019-08-15 | 2019-12-03 | 贵州永红航空机械有限责任公司 | A kind of air ejection device |
-
2021
- 2021-10-20 CN CN202111221190.6A patent/CN113958540B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190010962A1 (en) * | 2017-07-06 | 2019-01-10 | Altevac Llc | High efficiency aspirator for inflatable emergency slides |
| CN208619425U (en) * | 2018-06-15 | 2019-03-19 | 北京航空航天大学 | Bleed ring, injector and injection inflation system |
| CN110529438A (en) * | 2019-08-15 | 2019-12-03 | 贵州永红航空机械有限责任公司 | A kind of air ejection device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116571371A (en) * | 2023-07-06 | 2023-08-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Ejector device combining distributed two-dimensional spray pipe and traditional circumferential seam |
| CN116571371B (en) * | 2023-07-06 | 2023-09-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Ejector device combining distributed two-dimensional spray pipe and traditional circumferential seam |
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| Publication number | Publication date |
|---|---|
| CN113958540B (en) | 2023-06-13 |
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