阅读说明：本技术 一种u型管结构负压吸气式脉冲发动机 (Negative pressure air suction type pulse engine with U-shaped tube structure ) 是由 杨沐 周春晖 于 2021-08-12 设计创作，主要内容包括：本发明公开了一种U型管结构负压吸气式脉冲发动机,属于喷气发动机领域,包括U型管和燃料室,所述燃料室包括左侧燃料室和右侧燃料室,所述所述左侧燃料室和右侧燃料室的底部通过连接管相互连通,所述左侧燃料室和右侧燃料室的上部共同安装有燃烧套管,所述燃烧套管的内部从左至右依次设有相互连通的上回火燃烧室、一级燃烧室、混合燃料空气约束腔道和二级燃烧室,所述上回火燃烧室的左侧与U型管的上端连通,所述燃烧套管的右端安装有与二级燃烧室连通的上尾喷管。本发明的发动机通过U型管结构上下两层次多级燃烧室串联的设计,可提高燃料的燃烧效率,另外发动机的能效比高、结构简单、故障率低、部分零部件制造成本低。(The invention discloses a negative pressure air-breathing pulse engine with a U-shaped tube structure, which belongs to the field of jet engines and comprises a U-shaped tube and a fuel chamber, wherein the fuel chamber comprises a left fuel chamber and a right fuel chamber, the bottoms of the left fuel chamber and the right fuel chamber are mutually communicated through a connecting tube, the upper parts of the left fuel chamber and the right fuel chamber are jointly provided with a combustion sleeve, the interior of the combustion sleeve is sequentially provided with an upper tempering combustion chamber, a primary combustion chamber, a mixed fuel air constraint cavity channel and a secondary combustion chamber which are mutually communicated from left to right, the left side of the upper tempering combustion chamber is communicated with the upper end of the U-shaped tube, and the right end of the combustion sleeve is provided with an upper tail spray tube communicated with the secondary combustion chamber. The engine can improve the combustion efficiency of fuel by the design of connecting the upper and lower layers of secondary multi-stage combustion chambers in series through the U-shaped pipe structure, and has the advantages of high energy efficiency ratio, simple structure, low failure rate and low manufacturing cost of part of parts.)

1. The utility model provides a U type tubular construction negative pressure air-breathing pulse engine, includes U type pipe (1) and fuel room, its characterized in that, fuel room includes left side fuel room (3) and right side fuel room (4), the bottom of left side fuel room (3) and right side fuel room (4) is passed through connecting pipe (5) and is communicate each other, combustion sleeve (2) are installed jointly to the upper portion of left side fuel room (3) and right side fuel room (4), the inside of combustion sleeve (2) is equipped with last tempering combustion chamber (10), one-level combustion chamber (8), mixed fuel air restraint chamber way (16) and second grade combustion chamber (9) that communicate each other from a left side to the right side in proper order, the left side of last tempering combustion chamber (10) communicates with the upper end of U type pipe (1), last tail spray tube (6) that communicate with second grade combustion chamber (9) are installed to the right-hand member of combustion sleeve (2), the lower end of the U-shaped pipe (1) penetrates through the left fuel chamber (3) and is provided with a lower tempering combustion chamber (11), the outer side of the lower tempering combustion chamber (11) is sleeved with an installation pipe (20) fixed with the left fuel chamber (3), the surfaces of the upper tempering combustion chamber (10) and the lower tempering combustion chamber (11) are both provided with air holes in a penetrating mode, one end, far away from the left fuel chamber (3), of the lower tempering combustion chamber (11) is communicated with the lower tail spray pipe (7) to be installed, and the left end of the lower tail spray pipe (7) penetrates through the right fuel chamber (4) to be installed;

the left fuel chamber (3) is respectively provided with a liquid gasification one-way valve (15) corresponding to the combustion sleeve (2) and the mounting pipe (20), the right fuel chamber (4) is provided with a liquid gasification one-way valve (15) corresponding to the secondary combustion chamber (9), one end of the primary combustion chamber (8) close to the upper tempering combustion chamber (10) is provided with a fuel inlet (18), one end of the secondary combustion chamber (9) close to the mixed fuel air constraint cavity channel (16) is also provided with a fuel inlet (18), and spark plugs (19) are respectively arranged on the inner walls of the primary combustion chamber (8) and the secondary combustion chamber (9) and the positions close to the fuel inlets (18) on the same side;

install first water droplet shape air current restraint part (12) in first-stage combustion chamber (8), install second water droplet shape air current restraint part (13) in second grade combustion chamber (9), third water droplet shape air current restraint part (14) are installed to inside and the left side position department that is close to lower tempering combustion chamber (11) of U type pipe (1) lower extreme.

2. The negative-pressure air-breathing pulse engine with the U-shaped tube structure as claimed in claim 1, wherein the first water-drop-shaped airflow restriction member (12) is fixed to the inner wall of the primary combustion chamber (8) through a fin-shaped heat conduction connection column (17), the first water-drop-shaped airflow restriction member (12) is further fixed to a third water-drop-shaped airflow restriction member (14) through the fin-shaped heat conduction connection column (17), the fin-shaped heat conduction connection column (17) between the first water-drop-shaped airflow restriction member (12) and the third water-drop-shaped airflow restriction member (14) penetrates through the left-side fuel chamber (3), and the second water-drop-shaped airflow restriction member (13) is fixed to the inner wall of the secondary combustion chamber (9) through the fin-shaped heat conduction connection column (17).

3. The negative pressure air-breathing pulse engine with the U-shaped tube structure as claimed in claim 1, wherein a truncated cone-shaped hollow tube (21) is installed on one side of the lower tempering combustion chamber (11) close to the right side fuel chamber (4), and the lower tempering combustion chamber (11) is communicated with the lower tail nozzle (7) through the truncated cone-shaped hollow tube.

4. The negative-pressure air-breathing pulse engine with the U-shaped tube structure as claimed in claim 1, wherein the upper tempering combustion chamber (10) and the lower tempering combustion chamber (11) are both in a hollow tubular structure in a truncated cone shape, and the upper tempering combustion chamber (10) and the lower tempering combustion chamber (11) are both provided with air holes.

5. The negative-pressure air-breathing pulse engine with the U-shaped tube structure as claimed in claim 1, wherein the upper end of the left fuel chamber (3) is embedded and installed inside the combustion sleeve (2), the upper end of the combustion sleeve (2) is wrapped outside the primary combustion chamber (8), and the upper end of the right fuel chamber (4) is fixedly installed with the bottom wall of one end, close to the upper tail nozzle (6), of the combustion sleeve (2).

6. The negative-pressure air-breathing pulse engine with the U-shaped tube structure as claimed in claim 1, wherein the mixed fuel air restriction cavity (16) is of a circular truncated cone-shaped tube structure, one end, with a smaller diameter, of the mixed fuel air restriction cavity (16) is mounted with the primary combustion chamber (8), and one end, with a larger diameter, of the mixed fuel air restriction cavity (16) is mounted with the secondary combustion chamber (9).

7. A negative pressure air-breathing pulse engine with a U-tube structure according to claim 1, characterized in that eight spark plugs (19) are arranged around the inner wall of the primary combustion chamber (8), and eight spark plugs (19) are arranged around the inner part of the secondary combustion chamber (9).

Technical Field

The invention relates to the technical field of jet engines, in particular to a negative pressure air suction type pulse engine with a U-shaped tube structure.

Background

The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine.

The engine in the prior art still has the following technical defects in actual use: the invention provides a negative pressure air suction type pulse engine with a U-shaped pipe structure, which solves the technical problems that part of incompletely combusted fuel in an engine is delivered from an air inlet channel, the engine forms reverse flow to generate negative thrust and the fuel is not easy to heat.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a negative pressure air suction type pulse engine with a U-shaped tube structure.

In order to achieve the purpose, the invention adopts the following technical scheme:

a negative pressure air suction type pulse engine with a U-shaped tube structure comprises a U-shaped tube and a fuel chamber, wherein the fuel chamber comprises a left fuel chamber and a right fuel chamber, the bottoms of the left fuel chamber and the right fuel chamber are mutually communicated through a connecting tube, a combustion sleeve is jointly installed on the upper portions of the left fuel chamber and the right fuel chamber, an upper tempering combustion chamber, a primary combustion chamber, a mixed fuel air restraint cavity channel and a secondary combustion chamber which are mutually communicated are sequentially arranged in the combustion sleeve from left to right, the left side of the upper tempering combustion chamber is communicated with the upper end of the U-shaped tube, an upper tail spray tube communicated with the secondary combustion chamber is installed at the right end of the combustion sleeve, the lower end of the U-shaped tube penetrates through the left fuel chamber and is provided with a lower tempering combustion chamber, an installation tube fixed with the left fuel chamber is sleeved on the outer side of the lower tempering combustion chamber, and air holes are formed in the surfaces of the upper tempering combustion chamber and the lower tempering combustion chamber, one end of the lower tempering combustion chamber, which is far away from the left fuel chamber, is communicated with a lower tail nozzle, and the left end of the lower tail nozzle penetrates through the right fuel chamber;

the left fuel chamber is respectively provided with a liquid gasification one-way valve corresponding to the combustion sleeve and the mounting pipe, the right fuel chamber is provided with a liquid gasification one-way valve corresponding to the secondary combustion chamber, one end of the primary combustion chamber, which is close to the upper tempering combustion chamber, is provided with a fuel inlet, one end of the secondary combustion chamber, which is close to the mixed fuel air constraint cavity channel, is also provided with a fuel inlet, and spark plugs are arranged on the inner walls of the primary combustion chamber and the secondary combustion chamber and at positions close to the same side provided with the fuel inlets;

the first water-drop-shaped airflow restraint part is mounted in the first-stage combustion chamber, the second water-drop-shaped airflow restraint part is mounted in the second-stage combustion chamber, and the third water-drop-shaped airflow restraint part is mounted in the lower end of the U-shaped pipe and close to the left position of the lower tempering combustion chamber.

Furthermore, the first water-drop-shaped airflow restraint part is fixed to the inner wall of the primary combustion chamber through the fin-shaped heat conduction connecting column, the first water-drop-shaped airflow restraint part is fixed to the third water-drop-shaped airflow restraint part through the fin-shaped heat conduction connecting column, the fin-shaped heat conduction connecting column between the first water-drop-shaped airflow restraint part and the third water-drop-shaped airflow restraint part penetrates through the left fuel chamber, and the second water-drop-shaped airflow restraint part is fixed to the inner wall of the secondary combustion chamber through the fin-shaped heat conduction connecting column.

Furthermore, a circular truncated cone-shaped hollow pipe is installed on one side, close to the right fuel chamber, of the lower tempering combustion chamber, and the lower tempering combustion chamber is communicated with the lower tail jet pipe through the circular truncated cone-shaped hollow pipe.

Furthermore, the upper tempering combustion chamber and the lower tempering combustion chamber are both in a hollow tubular structure in a round table shape, and the upper tempering combustion chamber and the lower tempering combustion chamber are both provided with air holes.

Further, the upper end in left side fuel room is inlayed and is established the inside of installing at combustion sleeve, and combustion sleeve's upper end parcel is in the outside of one-level combustion chamber, the upper end in right side fuel room and combustion sleeve are close to the diapire fixed mounting of last tail-nozzle one end.

Furthermore, the mixed fuel air restraint cavity is of a circular truncated cone tubular structure, the end, with the smaller diameter, of the mixed fuel air restraint cavity is mounted with the first-stage combustion chamber, and the end, with the larger diameter, of the mixed fuel air restraint cavity is mounted with the second-stage combustion chamber.

Further, eight spark plugs are arranged on the inner wall of the primary combustion chamber in a surrounding mode, and eight spark plugs are also arranged on the inner portion of the secondary combustion chamber in a surrounding mode.

Compared with the prior art, the invention has the beneficial effects that:

1. the invention utilizes the air mixed fuel of two-stage compression deflagration of the upper tail nozzle and single-machine compression of the lower tail nozzle to improve the fuel utilization rate of the traditional pulse engine.

2. The invention has the advantages of high energy efficiency ratio, simple structure, low failure rate, low manufacturing cost of part of parts and the like.

3. The invention is beneficial to improving the combustion efficiency by the design of connecting the upper and lower layers of secondary multi-stage combustion chambers in series in the U-shaped pipe structure.

In conclusion, the engine provided by the invention has the advantages that the combustion efficiency of fuel can be improved through the design that the upper and lower layers of the multi-stage combustion chambers of the U-shaped pipe structure are connected in series, in addition, the energy efficiency ratio of the engine is high, the structure is simple, the failure rate is low, and the manufacturing cost of part of parts is low.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.

FIG. 1 is a schematic diagram of the overall structure of a negative pressure air-breathing pulse engine with a U-shaped tube structure according to the present invention;

FIG. 2 is an internal cross-sectional view of a negative pressure air-breathing pulse engine with a U-shaped tube structure according to the present invention;

FIG. 3 is a schematic view showing the installation of a U-shaped pipe, an upper tempering combustion chamber, a first drop-shaped airflow restriction member, a lower tempering combustion chamber and a lower tail pipe according to the present invention;

FIG. 4 is a schematic view showing the installation of the combustion liner, the left fuel tank, the connecting pipe and the right fuel tank in the present invention;

FIG. 5 is a schematic view of the installation of the secondary combustion chamber, the second drop shaped air flow restriction and the upper jet nozzle of the present invention;

FIG. 6 is a schematic view showing the external structure of a lower-tempering combustor in accordance with the present invention;

fig. 7 is an enlarged view of a portion a of fig. 2.

In the figure: the device comprises a 1U-shaped pipe, a 2 combustion sleeve, a 3 left side fuel chamber, a 4 right side fuel chamber, a 5 connecting pipe, a 6 upper tail nozzle, a 7 lower tail nozzle, a 8 primary combustion chamber, a 9 secondary combustion chamber, a 10 upper tempering combustion chamber, a 11 lower tempering combustion chamber, a 12 first water drop-shaped air flow restraint piece, a 13 second water drop-shaped air flow restraint piece, a 14 third water drop-shaped air flow restraint piece, a 15 liquid gasification one-way valve, a 16 mixed fuel air restraint cavity, a 17 fin-shaped heat conduction connecting column, a 18 fuel inlet, a 19 spark plug, a 20 mounting pipe and a 21 truncated cone-shaped hollow 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.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

Referring to fig. 1-7, a negative pressure air-breathing pulse engine with a U-shaped tube structure comprises a U-shaped tube 1 and a fuel chamber, wherein the fuel chamber comprises a left fuel chamber 3 and a right fuel chamber 4, the bottoms of the left fuel chamber 3 and the right fuel chamber 4 are mutually communicated through a connecting tube 5, a combustion sleeve 2 is jointly installed on the upper portions of the left fuel chamber 3 and the right fuel chamber 4, and an upper tempering combustion chamber 10, a primary combustion chamber 8, a mixed fuel air constraint cavity channel 16 and a secondary combustion chamber 9 which are mutually communicated are sequentially arranged in the combustion sleeve 2 from left to right.

The mixed fuel air constraint cavity channel 16 is in a circular truncated cone-shaped structure, one end, with a smaller diameter, of the mixed fuel air constraint cavity channel 16 is installed with the primary combustion chamber 8, and the other end, with a larger diameter, of the mixed fuel air constraint cavity channel 16 is installed with the secondary combustion chamber 9.

The upper end of the left fuel chamber 3 is embedded in the combustion sleeve 2, the upper end of the combustion sleeve 2 is wrapped outside the primary combustion chamber 8, and the upper end of the right fuel chamber 4 and the combustion sleeve 2 are fixedly mounted on the bottom wall close to one end of the upper tail jet pipe 6.

Go up the left side of tempering combustion chamber 10 and the upper end intercommunication of U type pipe 1, last tail-nozzle 6 with second grade combustion chamber 9 intercommunication is installed to the right-hand member of combustion sleeve 2, the lower extreme of U type pipe 1 passes left side fuel room 3 and installs lower tempering combustion chamber 11, the outside cover of lower tempering combustion chamber 11 is equipped with the installation pipe 20 fixed with left side fuel room 3, go up tempering combustion chamber 10 and lower tempering combustion chamber 11 and all be the hollow tubular structure of round platform shape, go up the surface of tempering combustion chamber 10 and lower tempering combustion chamber 11 and all run through and seted up the gas pocket.

One end of the lower tempering combustion chamber 11, which is far away from the left fuel chamber 3, is communicated with the lower tail nozzle 7, and the left end of the lower tail nozzle 7 penetrates through the right fuel chamber 4; one side of the lower tempering combustion chamber 11 close to the right fuel chamber 4 is provided with a circular truncated cone-shaped hollow pipe 21, and the lower tempering combustion chamber 11 is communicated with the lower tail jet pipe 7 through the circular truncated cone-shaped hollow pipe.

The left fuel chamber 3 is respectively provided with a liquid gasification one-way valve 15 corresponding to the combustion sleeve 2 and the mounting pipe 20, the right fuel chamber 4 is provided with a liquid gasification one-way valve 15 corresponding to the secondary combustion chamber 9, one end of the primary combustion chamber 8 close to the upper tempering combustion chamber 10 is provided with a fuel inlet 18, one end of the secondary combustion chamber 9 close to the mixed fuel air constraint cavity channel 16 is also provided with a fuel inlet 18, and the inner walls of the primary combustion chamber 8 and the secondary combustion chamber 9 and the positions close to the fuel inlet 18 on the same side are both provided with spark plugs 19; eight spark plugs 19 are arranged around the inner wall of the primary combustion chamber 8, and eight spark plugs 19 are also arranged around the inner part of the secondary combustion chamber 9.

A first water drop-shaped airflow restraint piece 12 is installed in the first-stage combustion chamber 8, a second water drop-shaped airflow restraint piece 13 is installed in the second-stage combustion chamber 9, and a third water drop-shaped airflow restraint piece 14 is installed in the lower end of the U-shaped pipe 1 and close to the left side of the lower tempering combustion chamber 11.

The first water-drop-shaped airflow restraint part 12 is fixed with the inner wall of the primary combustion chamber 8 through the fin-shaped heat conduction connecting column 17, the first water-drop-shaped airflow restraint part 12 is further fixed with the third water-drop-shaped airflow restraint part 14 through the fin-shaped heat conduction connecting column 17, the fin-shaped heat conduction connecting column 17 between the first water-drop-shaped airflow restraint part 12 and the third water-drop-shaped airflow restraint part 14 penetrates through the left fuel chamber 3 to be arranged, and the second water-drop-shaped airflow restraint part 13 is fixed with the inner wall of the secondary combustion chamber 9 through the fin-shaped heat conduction connecting column 17.

The working principle of the invention is as follows: left side fuel room 3 and right side fuel room 4 are respectively through liquid gasification check valve 15 to the interior input ethanol fuel of combustion sleeve 2, fuel inlet 18 has been seted up to one-level combustion chamber 8, fuel passes through fuel inlet 18 and gets into in one-level combustion chamber 8, spark plug 19 ignites, fuel deflagration in one-level combustion chamber 8, fuel inlet 18 has been seted up to same second grade combustion chamber 9, fuel passes through fuel inlet 18 and gets into in second grade combustion chamber 9, spark plug 19 ignites, fuel deflagration in second grade combustion chamber 9, the same deflagration of fuel in the combustion sleeve 2 this moment, and conduction through U type pipe 1, make upper tail spray tube 6 and lower tail spray tube 7 jet gas simultaneously.

At the moment of air injection, the primary combustion chamber 8 and the secondary combustion chamber 9 form negative pressure, so that air is sucked, mixed with fuel and detonated again, and the work is done repeatedly.

The space between the first-stage combustion chamber 8 and the second-stage combustion chamber 9 is a mixed fuel air constraint cavity channel 16 which is composed of a plurality of sections of hollow cavities in a circular truncated cone shape, so that the entering air is compressed and then expanded, and a vortex is easily formed after entering the combustion chamber, thereby being beneficial to promoting the mixing of the air and the fuel and improving the combustion efficiency.

When the primary combustion chamber 8 and the secondary combustion chamber 9 deflagrate and do work, the fuel in the left fuel chamber 3 and the right fuel chamber 4 can be heated, and the gasification of the fuel is promoted. Thrust is increased by reflecting the gas waves of the deflagration for multiple times.

The upper tail nozzle 6 is in a hollow round table shape, mixed fuel air of deflagration is compressed, and thrust can be effectively improved.

The upper and lower multi-stage combustion chambers realize the sufficient mixing of the gasified fuel and the air and form multiple times of detonation of the mixed fuel air.

The upper tempering combustion chamber 10 and the lower tempering combustion chamber 11 enable liquid fuel to be fully gasified, a large number of air holes are formed in the upper tempering combustion chamber 10 and the lower tempering combustion chamber 11, the contact area and the space are increased, oil and gas in the engine combustion chamber are uniformly distributed and fully combusted, and the working stability of the pulse engine can be improved.

The mixed fuel air deflagrated in the secondary combustion chamber 9 restricts the cavity channel 16, the area of the inlet section of the cavity channel is sharply reduced, the area of the outlet section of the cavity channel is enlarged, and the deflagration gas is restricted to generate thrust.

Eight spark plugs 19 in the primary combustion chamber 8 and the secondary combustion chamber 9 adopt intermittent ignition.

The upper tempering combustion chamber 10 and the lower tempering combustion chamber 11 can avoid the problem of flameout caused by overlarge air suction amount when air suction does work.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.