CN113958540B - Supersonic air injection device - Google Patents

Supersonic air injection device Download PDF

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Publication number
CN113958540B
CN113958540B CN202111221190.6A CN202111221190A CN113958540B CN 113958540 B CN113958540 B CN 113958540B CN 202111221190 A CN202111221190 A CN 202111221190A CN 113958540 B CN113958540 B CN 113958540B
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China
Prior art keywords
air
injection pipe
transition section
air duct
pipe
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CN202111221190.6A
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CN113958540A (en
Inventor
赵清
王田
卢继方
陈官林
陶刘远
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Guizhou Yonghong Aviation Machinery Co Ltd
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Guizhou Yonghong Aviation Machinery Co Ltd
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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
    • 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
    • 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)
  • Jet Pumps And Other Pumps (AREA)
  • Nozzles (AREA)

Abstract

The invention discloses a supersonic air injection device which mainly comprises a mounting plate, an air channel transition section, an injection pipe, a spray pipe, a secondary cooling air channel, a supporting plate and an inlet nozzle, wherein the injection pipe is centrally arranged in the air channel transition section, and the spray pipe is a Laval spray pipe which is symmetrically arranged. High-temperature high-pressure gas enters through the inlet nozzle, flows through the injection pipe, is sprayed out of the spray pipe to form a negative pressure area, sucks low-temperature air from the air inlet, mixes at the two cold air channels through the mounting plate and the air channel transition section, and flows out of the air outlet. The invention is used for injecting low-temperature air by utilizing high-temperature and high-pressure gas, and the injected low-temperature air can be used as a cold source supply device for heat dissipation. The jet pipe and the flow channel are more reasonable in layout, and the mixing uniformity of the jet air flow and the jet air flow is improved, so that the jet effect can be effectively improved.

Description

Supersonic air injection device
Technical Field
The invention relates to a supersonic air injection device, and belongs to the field of structural design of ejectors.
Background
In the ground stage of the aircraft, when low-temperature ambient air needs to be pumped as a cold source to dissipate heat of equipment, an ejector is often needed. The air outlet section of the ejector on the aircraft is short in length due to the limitation of the installation space, so that the air flows cannot be well mixed; when the ejector is provided with a plurality of spray pipes, the influence of Bernoulli effect is easily caused among a plurality of spray pipes, among the spray pipes and the wall surface of the flow channel, the mixing of air flow is further influenced, and finally the ejection effect is influenced.
The prior patent discloses a structure of an air injection device (CN 110529438A, 2019-12-03), but the air injection device is not applicable to occasions with higher space occupation requirements (namely, the injection device is required to be very small in size and regular in appearance requirement), on one hand, the injection device is influenced by Bernoulli effect, the injection device still has defects in the uniformity of mixing injection air flow and injected air flow, on the other hand, the unique C-shaped injection pipe structure and the distribution mode of a spray pipe easily generate larger air flow disturbance, the mixing area of injection air flow and injected air flow is passively reduced by the mode of the external injection pipe, the air flow mixing is uneven, in addition, serious air flow disturbance can be generated when the injection air flow speed is increased due to the asymmetry of the injection pipe, and welding seams exist between the injection pipe and an air duct shell, so that the air injection device is in an irregular shape and has higher processing requirements.
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 a good injection effect, reduces the disturbance of air flow, is suitable for the compact layout of the space on an aircraft, and greatly improves the injection effect of the air flow in a limited installation space.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
a supersonic air injection device comprises a mounting plate, an air channel transition section, an injection pipe, a spray pipe, a secondary cooling air channel and a support plate;
the air duct transition section is a variable cross-section shell with closed circumference and open two ends, one end of the air duct 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 duct transition section, a space is reserved between the injection pipe and the inner wall of the air duct 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 injection pipe, and the air flow inlet end of the spray pipes is communicated with the connecting holes on the injection pipe;
the two cooling air channels are connected with the tail end of the air outlet direction of the air channel transition section, and are straight pipelines with equal cross sections;
the backup pad is located the wind channel changeover portion inside, and is connected the injection pipe with the wind channel changeover portion.
Alternatively, a positioning hole is formed in the side face of the air duct transition section, and an inlet pipeline penetrates through the positioning hole and is connected with the injection pipe.
Alternatively, the inner surface of the transition section of the air duct 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.
Alternatively, the annular central axis of the ejector tube is parallel to the air flowing direction and coincides with the center of the air outlet end section of the air passage transition section, so that the annular surface of the ejector tube is positioned in the middle of the air outlet end section of the air passage transition section.
Alternatively, the circumferential profile of the ejector tube is in a kidney-shaped hole shape, a plurality of connecting holes are distributed at equal intervals along the contour line of the kidney-shaped hole shape, at least one connecting hole is formed in two circular arc sections of the contour of the kidney-shaped hole, and the connecting holes are all positioned on the annular surface of the ejector tube, which points to the air outflow end.
Alternatively, the spray pipe is a Laval spray pipe and is connected with the connecting hole on the injection pipe through a positioning structure.
Alternatively, the air flow direction of the spray pipe is consistent with the air flow direction in the two cold air channels.
Alternatively, the nozzle has an air flow inlet end angle greater than an air flow outlet end angle.
Alternatively, the mounting plate, the air duct transition section, the injection pipe, the spray pipe, the secondary cooling air duct, the support plate and the inlet nozzle are welded and connected.
In the invention, high-temperature high-pressure gas enters through the inlet nozzle, flows through the injection pipe, is sprayed out of the injection pipe to form a negative pressure area, sucks low-temperature air from the air inlet, mixes at the two cold air channels through the mounting plate and the air channel transition section, and flows out of the air outlet.
The invention is used for injecting low-temperature air by utilizing high-temperature and high-pressure gas, and the injected low-temperature air can be used as a cold source for heat dissipation of equipment on an aircraft. In consideration of the fact that the number of system equipment on the aircraft is large, pipelines are complex, the space is limited, and the structural compactness of the injection device is required to be improved, the air injection device is used as an injection cold source of the heat radiation device, is connected with a cold source outlet of the heat radiation device through a mounting plate, an inlet nozzle and a secondary cold air channel are connected with the system pipeline on the aircraft, and an annular injection pipe is arranged in a transition section of the air channel, so that the structural compactness of the injection device is improved, and the air injection device is suitable for narrow pipeline space layout on the aircraft.
The jet pipes of the invention are carefully calculated and verified in terms of selection (Laval jet pipes) and size, relative positions (space equidistant symmetrical arrangement) among the jet pipes and flow channel layout (section characteristics of an air channel transition section and a secondary cooling air channel), so that the influence of Bernoulli effect among jet flows can be reduced, the jet air flow and the jet air flow are well mixed, the jet effect is effectively improved, and the invention is particularly characterized in the following aspects:
firstly, the injection pipe adopts an annular design, so that the distribution mode of the spray pipes is spatially symmetrical, the Bernoulli effect is reduced, the mutual attraction degree of the spray flows of a plurality of spray pipes is reduced, the mixing uniformity degree of injection fluid and injected fluid is improved, and the air flow disturbance problem is correspondingly reduced;
secondly, the injection pipe is arranged in the air channel transition section, a space is reserved between the injection pipe and the inner wall of the air channel transition section, two mixed channels of injection air flow and injected air flow are formed, one channel is an annular injection pipe inner ring area, the other channel is a space between an annular injection pipe outer ring and the inner wall of the air channel transition section, the outlet end of the air channel transition section is connected with a secondary cooling air channel, meanwhile, the air channel transition section is designed into a mode that the cross section is changed from small to large, the mixed air channel area of injection fluid and injected fluid is increased (the injection air flow ejection speed is increased by matching with a Laval nozzle, the area of a negative pressure area is enlarged, the air channel mixed area is enlarged), and the disturbance of air flow is reduced;
thirdly, the spray pipe adopts the structural form of a Laval spray pipe, so that the jet speed of air flow is improved, and the injection effect is improved. The front half part of the Laval nozzle is a structure which is formed by reducing the cross section from a large cross section and shrinking the cross section to the throat from the small cross section to the large cross section, the throat is then changed from the small cross section to the large cross section and expands outwards, high-pressure gas flows into the front half part of the nozzle and passes through the throat to be sprayed out from the rear half part, the nozzle design ensures that the speed of the gas flow is changed due to the change of the cross section area, the flow speed of the gas flow is changed from subsonic to sonic until the speed of the gas flow is accelerated to supersonic speed, the spraying of supersonic fluid generates huge thrust, the negative pressure area is enlarged, and meanwhile, the negative pressure is increased, so that the injection effect is greatly improved in a limited space;
fourthly, the spray pipes are symmetrically arranged at equal intervals in space and are positioned in the middle of the transition section of the air duct and the secondary cooling air duct, and the distribution mode prevents the spray flows of the adjacent spray pipes from attracting each other, so that the uniformity of the spray flows in space is improved;
fifthly, the ejector pipe is arranged in the middle position of the air duct (the section of the air flow outlet is centered), the shape of the ejector pipe is annular, and meanwhile, the section shape of the air duct (the air duct transition section and the two cold air ducts) is of an annular structure as well as the space layout of the spray pipe, so that the influence of Bernoulli effect on the jet flow and the wall surface of the air duct is not easy to cause; on the other hand, the area of the air duct mixing the injection fluid and the injected fluid is increased by adopting the air duct transition section with the variable cross section from small to large, so that the problem that the jet flow and the air duct wall surface are easily influenced by Bernoulli effect is also reduced;
sixth, adopt the mode that backup pad connected wind channel changeover portion and injection pipe to reduce the processing degree of difficulty, avoided irregular welding seam to appear, improved injection device's operational reliability.
Drawings
FIG. 1 is a schematic view of the mounting structure of a supersonic jet apparatus of the present invention;
FIG. 2 is a left side view of FIG. 1;
FIG. 3 is a schematic view of the mounting plate of the present invention;
FIG. 4 is a schematic diagram of a transition section of an air duct according to the present invention;
FIG. 5 is a schematic view of the structure of the ejector tube of the present invention;
FIG. 6 is a schematic view of a nozzle structure according to the present invention;
FIG. 7 is a schematic diagram of a secondary air duct structure according to the present invention;
FIG. 8 is a schematic view of a support plate structure according to the present invention;
FIG. 9 is a schematic view of the inlet nozzle structure of the present invention;
in the figure: 1-mounting plate, 2-air duct transition section, 3-injection pipe, 4-spray pipe, 5-secondary cooling air duct, 6-support plate and 7-inlet nozzle.
Detailed Description
The present invention will be further described with reference to the drawings and the specific embodiments, but it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made according to the ordinary skill and familiar means of the art to which this invention pertains are included within the scope of the present invention without departing from the above technical idea of the invention.
In the embodiment, as shown in fig. 1 to 9, the supersonic air injection device comprises a mounting plate 1, an air duct transition section 2, an injection pipe 3, a spray pipe 4, a secondary cooling air duct 5, a support plate 6 and an inlet nozzle 7. All the components of the injection device are connected together through 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 through welding; the assembly positions of the injection pipe 3, the spray pipe 4 and the inlet nozzle 7 shown in fig. 5, 6 and 9 comprise positioning structures, and the three are assembled and welded into a whole; the air duct transition section 2 and the injection pipe 3 shown in fig. 4 and 5 are welded together through positioning holes and inlet pipelines; the air duct transition section 2, the injection pipe 3 and the supporting plate 6 shown in fig. 4, 5 and 8 are welded together through positioning grooves.
As shown in fig. 1, the annular injection pipe 3 is positioned in the middle of the cross section of the air duct transition section 2, and the annular area of the injection pipe 3 is smaller than the cross section of the air duct transition section 2, so that the air duct is split into an inner annular channel of the injection pipe 3 and an outer annular channel between the injection 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 position of the mounting plate, the injection device is mounted on equipment through the mounting plate 1, and low-temperature air is introduced.
As shown in fig. 4, the air duct transition section 2 is a circumferential closed shell with a gradually widened cross section, a variable cross section channel for air inflow and outflow is formed, the injected ambient air enters the injection device through an air inlet (the position indicated by the left arrow in fig. 2), and 1 positioning hole is formed in the air duct transition section 2 and used 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 injected air flow and the injected air flow, reduces air flow disturbance, and the injected air flow are mixed in a closed space formed by the air duct transition section 2 and the two cold air ducts 5 and are not influenced by air flow disturbance of the external environment.
As shown in fig. 5, the ejector tube 3 is a kidney-shaped hole-shaped annular pipeline, and the outer circumferential surface of the airflow outlet is provided with connecting holes for connecting with the spray tube 4, and in fig. 5, 14 connecting holes are shown, and the connecting holes are located on a plane and are distributed on the contour line of the kidney-shaped hole at equal intervals, wherein 1 connecting hole is respectively arranged at the middle position of two circular arc sections of the contour line of the kidney-shaped hole. The injection pipe 3 is assembled with the spray pipe 4 through a connecting hole and welded and sealed. The ejector tube 3 is located inside the air duct transition section 2, the normal line of the plane where the 14 connecting holes are located is parallel to the air flow direction of the ejector device, and the midpoint of the kidney-shaped hole-shaped outline where the 14 connecting holes are located (namely, the midpoint of the ejector tube 3 in fig. 1 coincides with the middle position of the air outlet end section of the air duct transition section 2, so that the ejector tube 3 in fig. 1 is just located in 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 14 spray pipes 4 are symmetrically distributed in a space distribution mode, so that the flow field generated in the symmetrical distribution mode is more uniform in distribution and better in injection effect.
As shown in fig. 6, the nozzle 4 is a laval nozzle, the angle a of the air flow inlet end of which is larger than the angle b of the air flow outlet end.
As shown in fig. 6, the nozzle 4 is a laval nozzle, and the angle of the air flow inlet end of the nozzle 4 is larger than the angle of the air flow outlet end. The spray pipe 4 contains location structure, U type structure (the U profile in oval region A in FIG. 6) of junction promptly, and the U profile of spray pipe 4 assembles and welds sealedly with the connecting hole on the outer periphery of injection pipe 3, reduces the probability that injection pipe 3 leaks gas, guarantees the stability of injection pipe 3 regional air current, avoids appearing the air current disturbance by a wide margin. The Laval nozzle is adopted, so that the speed of an ejected airflow outlet can be greatly improved to supersonic speed, and the ejection effect is improved.
As shown in fig. 7, the secondary cooling air duct 5 is a straight pipeline with a uniform cross section, and is connected with the air outlet end of the air duct transition section 2, so as to achieve the purpose of fully mixing high-temperature high-pressure air and injected low-temperature air.
As shown in fig. 4 and 8, 6 support plates 6 connect the air duct transition section 2 and the injection pipe 3 into a whole through 6 positioning grooves on the air duct transition section 2.
As shown in fig. 9, the inlet nozzle 7 is installed on the apparatus, and high-temperature and high-pressure air is introduced.
In the invention, the injection pipe 3 is an annular circular section pipe, the spray pipes 4 are symmetrically distributed on the airflow outflow section of the injection pipe 3 at equal intervals, the area of an air channel for mixing injection fluid and injected fluid is increased, the whole air channel is a regular and approximately symmetrical annular straight air channel (the air channel transition section 2 and the secondary cooling air channel 5 are combined to form), and the structural design is beneficial to reducing turbulent flow and improving the airflow mixing effect. Compared with an external mode, the mode of the internal injection pipe 3 reduces the disturbance influence of the external environment air flow on one hand and increases the mixing cross section area of the injection air flow and the injected air flow on the other hand under the condition that the same space is occupied.
The above embodiments are not intended to limit the scope of the present invention, and all modifications, or equivalent substitutions made on the basis of the technical solutions of the present invention should fall within the scope of the present invention.

Claims (5)

1. A supersonic air ejector, characterized in that: comprises a mounting plate (1), an air duct transition section (2), an injection pipe (3), a spray pipe (4), a secondary cooling air duct (5) and a supporting plate (6);
the air duct transition section (2) is a variable cross-section shell with closed circumference and open two ends, one end of the air duct transition section (2) is connected with the mounting plate (1) to form a transition channel with a cross section gradually widened from the air inflow direction to the air outflow direction;
the inner surface of the air duct transition section (2) is provided with a plurality of positioning grooves, one end of the supporting plate (6) is arranged in each positioning groove, and the other end of the supporting plate (6) is connected with the annular peripheral surface of the injection pipe (3);
the injection pipe (3) is in a closed ring shape and is arranged in the air duct transition section (2), a space is reserved between the injection pipe (3) and the inner wall of the air duct 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 annular central axis of the injection pipe (3) is parallel to the air flow direction and coincides with the center of the air outlet end section of the air channel transition section (2), so that the annular surface of the injection pipe (3) is positioned in the middle of the air outlet end section of the air channel transition section (2);
the circumferential profile of the ejector pipe (3) is in a waist-shaped hole shape, a plurality of connecting holes are uniformly distributed along the contour line of the waist-shaped hole shape, at least one connecting hole is formed in two circular arc sections of the contour of the waist-shaped hole, and the connecting holes are all positioned on the annular surface of the ejector pipe (3) pointing to the air outflow end;
the spray pipes (4) are uniformly distributed along the annular peripheral surface of the injection pipe (3), and the air flow inlet end of the spray pipes (4) is communicated with the connecting holes on the injection pipe (3);
the spray pipe (4) is a Laval spray pipe and is connected with a connecting hole on the injection pipe (3) through a positioning structure;
the angle of the air flow inlet end of the spray pipe (4) is larger than the angle of the air flow outlet end;
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 constant cross section;
the supporting plate (6) is positioned inside the air duct transition section (2), and the injection pipe (3) is connected with the air duct transition section (2).
2. A supersonic air jet apparatus according to claim 1, wherein: the side face of the air duct transition section (2) is provided with a positioning hole, and an inlet pipeline penetrates through the positioning hole and is connected with the injection pipe (3).
3. A supersonic air jet apparatus according to claim 1, wherein: the injection pipe (3) is connected with an inlet nozzle (7) through an inlet pipeline.
4. A supersonic air jet apparatus according to claim 1, wherein: the air flow direction of the spray pipe (4) is consistent with the air flow direction in the secondary cooling air duct (5).
5. A supersonic air jet apparatus according to claim 1, wherein: the mounting plate (1), the air duct transition section (2), the injection 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.
CN202111221190.6A 2021-10-20 2021-10-20 Supersonic air injection device Active CN113958540B (en)

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Application Number Priority Date Filing Date Title
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CN113958540B true CN113958540B (en) 2023-06-13

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Publication number Priority date Publication date Assignee Title
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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US11333174B2 (en) * 2017-07-06 2022-05-17 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
CN110529438B (en) * 2019-08-15 2020-10-30 贵州永红航空机械有限责任公司 Air injection device

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