阅读说明：本技术 一种微型涡喷发动机的引射器 (Ejector of miniature turbojet engine ) 是由 郑登强 杨丛毅 窦洋 于 2021-09-18 设计创作，主要内容包括：一种微型涡喷发动机的引射器,包括用于尾喷口连接的接口管,所述接口管的左端为进气端,右端为排气端；还包括筒体,所述筒体为右端敞口状的中空结构,所述接口管的右端从所述筒体的左端插入并延伸至筒体的内腔中；所述筒体与所述接口管通过支板连接；所述支板、筒体与所述接口管形成一个半封闭的腔体；在所述筒体上设置有至少一个进料管；所述进料管连通至所述腔体。该引射器可以有效地降低尾喷口喷出的燃气气流的温度,实现了料剂进入引射器与高温高速燃气掺混均匀地扩散至大气中,提高引射系数；同时也能减少总压的损失而造成推力性能下降。(An ejector of a micro turbojet engine comprises a connector tube used for connecting a tail nozzle, wherein the left end of the connector tube is an air inlet end, and the right end of the connector tube is an exhaust end; the cylinder body is of a hollow structure with an open right end, and the right end of the mouthpiece is inserted into the inner cavity of the cylinder body from the left end of the cylinder body and extends into the inner cavity of the cylinder body; the barrel is connected with the interface tube through a support plate; the support plate, the cylinder body and the interface tube form a semi-closed cavity; at least one feeding pipe is arranged on the cylinder body; the feed pipe is communicated to the cavity. The ejector can effectively reduce the temperature of gas flow sprayed out from the tail nozzle, so that a material agent enters the ejector and is uniformly mixed with high-temperature high-speed gas to be diffused into the atmosphere, and the ejection coefficient is improved; meanwhile, the loss of total pressure can be reduced to cause the reduction of thrust performance.)

1. The utility model provides a miniature turbojet engine's ejector which characterized in that: the exhaust nozzle comprises a mouthpiece (10) used for connecting with a tail nozzle, wherein the left end of the mouthpiece (10) is an air inlet end, and the right end of the mouthpiece is an exhaust end; the cylinder body (20) is of a hollow structure with an open right end, and the right end of the mouthpiece (10) is inserted into the inner cavity of the cylinder body (20) from the left end of the cylinder body (20) and extends into the inner cavity of the cylinder body (20); the barrel (20) is connected with the mouthpiece (10) through a support plate (24); the support plate (24), the cylinder body (20) and the interface tube (10) form a semi-closed cavity (30); at least one feeding pipe (40) is arranged on the barrel body (20); the feed tube (40) is connected to the cavity (30).

2. The ejector of a micro turbojet engine as recited in claim 1, wherein: the cylinder body (20) comprises a contraction pipe (21), a mixing pipe (22) and a support plate (24); the contraction tube (21) is of a conical ring structure, and the diameter of the contraction tube (21) is gradually reduced from left to right; the support plate (24) is arranged at the left end of the shrinkage pipe (21); the mixing pipe (22) is of a straight-cylinder annular structure, and the left end of the mixing pipe (22) is connected with the right end of the contraction pipe (21).

3. The ejector of the micro turbojet engine according to claim 2, wherein: the right end face of the mouthpiece (10) is positioned in the inner cavity of the left half section of the mixing tube (22).

4. The ejector of the micro turbojet engine according to claim 2, wherein: a diffusion pipe (23) is arranged at the right end of the mixing pipe (22), the diffusion pipe (23) is of a conical ring structure, and the diameter of the diffusion pipe (23) is gradually increased from left to right; the diffusion pipe (23) and the mixing pipe (22) are integrally formed.

5. The ejector of the micro turbojet engine according to claim 2, wherein: the feeding pipe (40) is arranged on the shrinkage pipe (21), and the central line of the feeding pipe (40) is perpendicular to the outer surface of the shrinkage pipe (21).

6. The ejector of a micro turbojet engine as recited in claim 1, wherein: the mouthpiece (10) comprises an interface ring (11), an outlet ring (13) and a mouth-piece ring (12); the closing ring (12) is of a conical ring structure, and the diameter of the closing ring is gradually reduced from left to right; the interface ring (11) is arranged at the left end of the closing ring (12), and the outlet ring (13) is arranged at the right end of the closing ring (12).

7. The ejector of a micro turbojet engine according to claim 6, wherein: the interface ring (11), the closing-in ring (12) and the outlet ring (13) are integrally formed.

8. The ejector of a micro turbojet engine according to claim 6, wherein: a fixed snap ring (14) is arranged on the interface ring (11).

9. The ejector of a micro turbojet engine as recited in claim 1, wherein: the support plate (21) is of an annular structure, and the interface tube (10) is arranged on an inner hole of the support plate (21).

10. The ejector of a micro turbojet engine as recited in claim 1, wherein: the number of the feeding pipes (40) is one.

Technical Field

The invention relates to the technical field of turbojet engines, in particular to an ejector of a miniature turbojet engine.

Background

The air compressor of the micro turbojet engine compresses air, then the air enters a combustion chamber of the micro turbojet engine to be mixed and combusted with fuel oil, high-temperature and high-speed fuel gas is generated, and the high-temperature and high-speed fuel gas is discharged from a tail nozzle of the micro turbojet engine. Meanwhile, the generated high-temperature high-speed gas flow is relatively non-concentrated, the distribution field is asymmetric, the temperature is relatively high, structural damage can be caused to the refractory materials (such as chemical powder) and the turbojet engine body cannot be structurally mixed with other materials such as powder and liquid.

Disclosure of Invention

The invention mainly aims to provide an ejector of a micro turbojet engine, and aims to solve the technical problem.

In order to achieve the purpose, the invention provides an ejector of a micro turbojet engine, which comprises a connector tube used for connecting a tail nozzle, wherein the left end of the connector tube is an air inlet end, and the right end of the connector tube is an exhaust end; the cylinder body is of a hollow structure with an open right end, and the right end of the mouthpiece is inserted into the inner cavity of the cylinder body from the left end of the cylinder body and extends into the inner cavity of the cylinder body; the barrel is connected with the interface tube through a support plate; the support plate, the cylinder body and the interface tube form a semi-closed cavity; at least one feeding pipe is arranged on the cylinder body; the feed pipe is communicated to the cavity.

Preferably, the cartridge comprises a shrink tube, a mixing tube and a support plate; the shrinkage pipe is of a conical ring structure, and the diameter of the shrinkage pipe is gradually reduced from left to right; the support plate is arranged at the left end of the contraction pipe; the mixing tube is of a straight-tube annular structure, and the left end of the mixing tube is connected with the right end of the shrinkage tube.

Preferably, the right end face of the mouthpiece is located in the inner cavity of the left half section of the mixing tube.

Preferably, a diffusion pipe is arranged at the right end of the mixing pipe, the diffusion pipe is in a conical ring structure, and the diameter of the diffusion pipe is gradually increased from left to right; the diffusion pipe and the mixing pipe are integrally formed.

Preferably, the feed pipe is arranged on the shrink tube, and the center line of the feed pipe is perpendicular to the outer surface of the shrink tube.

Preferably, the mouthpiece includes an interface ring, an outlet ring and a mouth-piece ring; the closing ring is of a conical ring structure, and the diameter of the closing ring is gradually reduced from left to right; the interface ring is arranged at the left end of the closing ring, and the outlet ring is arranged at the right end of the closing ring.

Preferably, the interface ring, the closing-in ring and the outlet ring are integrally formed.

Preferably, a fixing snap ring is provided on the interface ring.

Preferably, the support plate is of an annular structure, and the interface tube is arranged on an inner hole of the support plate.

Preferably, the number of the feeding pipes is one. .

The invention has the following beneficial effects:

(1) the ejector provided by the invention is arranged on the tail nozzle of the micro turbojet engine, when mixing and ejecting are carried out, part of air in the feeding device enters the ejector under the action of negative pressure and is pre-mixed with the material agent conveyed from the feeding pipe for one time, so that the pre-mixed material agent is mixed with main fuel gas, and the temperature of the main fuel gas flow is reduced; the blended gas stream transports the agent to the atmosphere. The ejector can effectively reduce the temperature of gas flow sprayed out from the tail nozzle, so that a material agent enters the ejector and is uniformly mixed with high-temperature high-speed gas to be diffused into the atmosphere, and the ejection coefficient is improved; meanwhile, the loss of total pressure can be reduced to cause the reduction of thrust performance.

(2) Because the inlet pipe sets up on the shrink tube, can carry out the pre-mixing in the shrink tube when the material agent gets into, can effectively reduce the length of hybrid tube, greatly shorten the size of whole ejector.

(3) The left end of the contraction pipe and the support plate form a closed end, the right end of the contraction pipe is an open end, after the micro turbojet engine starts to work, a Venturi effect is formed at the right end of the contraction pipe, gas in a cavity formed by the contraction pipe, the connector pipe and the support plate is injected into the mixing pipe, meanwhile, the negative pressure value in the cavity formed by the contraction pipe, the connector pipe and the support plate is increased, and the material conveying capacity of the feeding pipe is enhanced; simultaneously because the shrink tube is the toper ring structure, the right-hand member area is less than the left end area far away, can accelerate the pressure boost when the air current passes through, further strengthens the negative pressure in the cavity that shrink tube, mouth-piece and crown plate constitute jointly. In addition, the diffusion pipe is arranged and is of a conical ring structure, the outlet area of the diffusion pipe is larger than the inlet area, when fuel gas mixed with the fuel agent is discharged, the airflow angle can be enlarged, and the distribution area is widened.

(4) The mouth-closing ring in the mouthpiece is of a conical ring structure, the area of the air inlet end is larger than that of the air outlet end, the flow rate of the outlet of the mouthpiece is improved, the Venturi effect formed at the position of the contraction tube is enhanced, and the temperature of fuel gas at the outlet of the mouthpiece can be further reduced.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

FIG. 1 is a front view of an eductor for a micro turbojet engine according to the present invention;

FIG. 2 is a schematic structural diagram of a mouthpiece in an injector of a micro turbojet engine according to the present invention;

FIG. 3 is a schematic view of the direction of air intake and feeding when the ejector of the micro turbojet engine provided by the invention works;

the reference numbers illustrate: 10-a mouthpiece; 11-interface ring; 12-a collar; 13-an outlet ring; 14-fixing the snap ring; 20-barrel body; 21-a shrink tube; 22-a mixing tube; 23-a diffuser tube; 24-a support plate; 30-a cavity; 40-feeding pipe.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

As shown in fig. 1 and 2, the ejector of the micro turbojet engine comprises a mouthpiece 10 for connection with a tail nozzle, wherein the left end of the mouthpiece 10 is an air inlet end, and the right end of the mouthpiece is an air outlet end; the barrel body 20 is of a hollow structure with an open right end, and the right end of the mouthpiece 10 is inserted into the inner cavity of the barrel body 20 from the left end of the barrel body 20 and extends into the inner cavity of the barrel body 20; the barrel body 20 is connected with the mouthpiece 10 through a support plate 24; the support plate 24, the cylinder body 20 and the mouthpiece 10 form a semi-closed cavity 30; at least one feed pipe 40 is arranged on the barrel 20; the feed tube 40 communicates with the cavity 30.

In this embodiment, the cartridge 20 includes a shrink tube 21, a mixing tube 22, and a strip 24; the shrinkage pipe 21 is of a conical ring structure, and the diameter of the shrinkage pipe 21 is gradually reduced from left to right; the support plate 24 is arranged at the left end of the shrinkage tube 21; the mixing tube 22 is a straight-tube annular structure, and the left end of the mixing tube 22 is connected with the right end of the shrinkage tube 21. The feed pipe 40 is arranged on the shrink tube 21, and the center line of the feed pipe 40 is perpendicular to the outer surface of the shrink tube 21. Because the inlet pipe 40 sets up on shrink tube 21, can carry out the pre-mixing in shrink tube 21 when the material agent gets into, can effectively reduce mixing tube 22's length, greatly shorten the size of whole ejector.

In this embodiment, the right end face of the mouthpiece 10 is located in the inner cavity of the left half of the mixing tube 22. That is, in the horizontal direction, the right end of the mouthpiece 10 is inserted from the left end of the barrel 20 and extends into the inner cavity of the left half section of the mixing tube 22. The feed agent from the feed pipe 40 reaches the mixing pipe to be mixed with the high-temperature high-speed fuel gas, and the air reaches the mixing pipe through the air inlet pipe to be mixed with the high-temperature high-speed fuel gas.

In the present embodiment, a diffuser 23 is disposed at the right end of the mixing tube 22, the diffuser 23 has a conical ring structure, and the diameter of the diffuser 23 gradually increases from left to right; the diffusion pipe 23 and the mixing pipe 22 are integrally formed. The outlet area of the diffuser 22 is larger than the inlet area, so that the airflow angle can be enlarged and the spreading area can be widened when the fuel gas mixed with the fuel agent is discharged.

In this embodiment, the mouthpiece 10 includes an interface ring 11, an outlet ring 13, and a mouth ring 12; the closing ring 12 is a conical ring structure and the diameter of the closing ring gradually decreases from left to right; the interface ring 11 is disposed at the left end of the closing ring 12, and the outlet ring 13 is disposed at the right end of the closing ring 12. The closing ring 12 is in a conical ring structure, the area of the air inlet end of the closing ring is larger than that of the air outlet end of the closing ring, the flow rate of the outlet of the mouthpiece 10 is improved, the Venturi effect formed at the position of the contraction tube 21 is enhanced, and the temperature of fuel gas at the outlet of the mouthpiece can be further reduced.

In this embodiment, the interface ring 11, the closing-in ring 12 and the outlet ring 13 are integrally formed. The integral forming is adopted, the structure is simple, the processing and the manufacturing are convenient, and meanwhile, the sealing performance of the whole interface tube 10 can be improved.

A fixing snap ring 14 is provided on the interface ring 11. The fixed clamping ring 14 is arranged to facilitate clamping of the mouthpiece 10 with the tail nozzle of the micro turbojet engine, and installation is simple and rapid.

As shown in fig. 3, the working principle of the present invention is: the ejector provided by the invention is arranged on the tail nozzle of a micro turbojet engine, when mixing and ejecting are carried out, the material agent enters the ejector under the action of negative pressure in a cavity 30 formed by the contraction pipe 21, the connector pipe 10 and the support plate 24, meanwhile, because the left end of the contraction pipe 21 and the support plate 24 form a closed end and the right end is an open end, a Venturi effect is formed at the right end of the contraction pipe 21, the material agent pre-mixed in the cavity 30 formed by the contraction pipe 21, the connector pipe 10 and the support plate 24 is brought into the mixing pipe 22, the pre-mixed material agent and main fuel gas are mixed in the mixing pipe 22, and the temperature of main fuel gas airflow is reduced; the blended gas stream transports the agent to the atmosphere.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.