CN203962199U - A kind of high-frequency pulse pinking combustion-powered apparatus - Google Patents

Abstract

A high-frequency pulse detonation combustion power device, including a pulse detonation combustion chamber connected in sequence from left to right, an exhaust nozzle and a multi-stage series booster structure; wherein, the pulse detonation combustion chamber includes The combustion chamber head end cover, the combustion chamber ignition section, the combustion chamber detonation section and the combustion chamber detonation section, the right end of the combustion chamber detonation section is connected with the tail nozzle; the combustion chamber head end cover is provided with a main nozzle, the main The nozzle is provided with the main nozzle air pipeline and the main nozzle fuel pipeline; the ignition section of the combustion chamber is provided with spark plugs on the circumference; , the auxiliary nozzle is provided with an auxiliary nozzle air pipeline and an auxiliary nozzle fuel pipeline. The utility model can reduce the filling time of the combustion chamber, increase the working frequency of the engine, and increase the thrust generated by the engine per unit time; in addition, a multi-stage series boosting structure is designed on the tail nozzle to further increase the thrust of the engine.

Description

A high-frequency pulse detonation combustion power device

【Technical field】

The utility model relates to the technical field of engines, in particular to a high-frequency pulse detonation combustion power device.

【Background technique】

Detonation combustion is another way of combustion. It is different from the slow combustion process. The detonation combustion process is very fast and can generate supersonic combustion waves, that is, detonation waves. The propagation of the detonation wave is realized by the strong impact and compression of the detonable mixture layer by layer by the shock wave to cause a high-speed chemical reaction. Therefore, the detonation wave can be considered as a strong shock wave coupling chemical reactions. The propagation velocity of detonation combustion is far greater than that of slow combustion, generally on the order of 10 ³ m/s. Compared with slow combustion combustion, detonation combustion has the advantages of self-pressurization, fast flame propagation speed, high combustion efficiency, and low pollutant emission. The detonation combustion replaces the isobaric combustion in traditional power plants, and the development is based on the detonation cycle. The new power plant can improve the efficiency of the use of existing energy.

Pulse detonation engine is a new concept propulsion device that uses intermittent detonation combustion to generate high temperature and high pressure gas to generate thrust. Pulse detonation engines are divided into air-breathing pulse detonation engines and rocket-type pulse detonation engines according to whether they have their own oxidant. There are two ways of detonation combustion initiation: direct detonation and indirect detonation. The former requires huge ignition energy, while the latter gradually forms a detonation wave through the transition from deflagration to detonation. The detonation wave is finally formed through the interaction between the flame and the compression wave in the detonation chamber. The distance from deflagration to detonation is called DDT. The length of DDT is mainly determined by parameters such as the size of the combustion chamber and the characteristics of the fuel. Considering the practicality, the pulse detonation engine generally adopts indirect detonation to obtain the detonation wave, which makes the length of the combustion chamber must be greater than the DDT. In order to ensure that most of the fuel in the combustion chamber releases heat by detonation combustion, the general design 4 to 5 times the distance of DDT. However, both the traditional air-breathing and rocket-type pulse detonation engines use air intake from the head of the pulse detonation combustion chamber, which affects the filling time of the combustion chamber to some extent, causing the engine operating frequency to vary with time. Decreases with increasing combustion chamber length. At the same time, because the working frequency of the pulse detonation engine is not high, compared with the traditional isobaric combustion chamber which has been in the filling and burning state, the combustion chamber of the traditional pulse detonation engine is filled with less fuel per unit time, resulting in the pulse detonation engine unit The thrust produced in a short period of time is low, which has prevented the application pace of the pulse detonation engine.

The review shows that although the detonation combustion has advantages compared with the traditional isobaric combustion, the pulse detonation engine still has the following main problems: 1) The pulse detonation engine has low operating frequency and is easily limited by the length of the combustion chamber; 2) The pulse detonation engine produces less thrust per unit time.

【Content of utility model】

The purpose of the utility model is to solve the problems of low operating frequency of the traditional pulse detonation engine, the frequency is limited by the length of the combustion chamber, and the thrust generated by the engine per unit time is small, and provides a high-frequency pulse detonation combustion power device, which can shorten the pulse The filling time of the detonation combustion chamber increases the thrust generated by the engine per unit time, and at the same time solves the problem that the operating frequency of the engine is limited by the length of the combustion chamber.

In order to achieve the above object, the technical solution adopted by the utility model is:

A high-frequency pulse detonation combustion power device, including a pulse detonation combustion chamber, a tail nozzle and a multi-stage series booster structure connected in sequence from left to right; wherein,

The pulse detonation combustion chamber includes the combustion chamber head end cover, the combustion chamber ignition section, the combustion chamber detonation section and the combustion chamber detonation section connected in sequence from left to right. The right end of the combustion chamber detonation section is connected with the tail nozzle; The main nozzle is arranged on the end cover of the chamber head, and the main nozzle is provided with the main nozzle air pipeline and the main nozzle fuel pipeline; the ignition section of the combustion chamber is provided with a spark plug on the circumference; the detonation section of the combustion chamber and the detonation section of the combustion chamber A number of auxiliary nozzles are equidistantly arranged in the circumferential direction along the axial direction, and auxiliary nozzle air pipelines and auxiliary nozzle fuel pipelines are arranged on the auxiliary nozzles.

The utility model is further improved in that: the tail nozzle is a convergent nozzle, the shrinkage ratio is 1.2 to 1.5, and the convergence angle is 6 to 10 degrees.

The utility model is further improved in that: the multi-stage serial booster structure includes a first-stage booster, a second-stage booster and a third-stage booster connected in sequence from left to right.

The utility model is further improved in that: the first-stage booster includes a first arc-shaped air intake end face and a first axisymmetric direct injection pipe, and the second-stage booster includes a second arc-shaped air intake end face and a second axisymmetric direct injection pipe , the three-stage booster includes a third arc-shaped intake end face and a third axisymmetric direct injection pipe; several multi-stage series booster structure connecting rods are evenly arranged in the circumferential direction of the first arc-shaped intake end face, and several multi-stage series One end of the booster structure support plate is connected to the corresponding multi-stage serial booster structure connecting rod, and the other end is connected to the tail of the pulse detonation combustion chamber; In the circumferential direction of the gas end surface, one end of several first interstage booster support plates is connected to the corresponding first interstage booster connecting rod, and the other end is connected to the first axisymmetric straight nozzle; several second interstage The booster connecting rods are evenly arranged in the circumferential direction of the third arc-shaped intake end face, one end of several second inter-stage booster support plates is connected to the corresponding second inter-stage booster connecting rods, and the other end is connected to the second inter-stage booster connecting rods. The two axisymmetric direct injection pipes are connected.

The utility model is further improved in that: the number of the multi-stage series booster structure support plate and the multi-stage series series booster structure connecting rod is 4, and the first inter-stage booster support plate and the first inter-stage booster connecting rod The quantity of each is 4, and the number of the support plate of the second interstage booster and the number of the connecting rods of the second interstage booster are both four.

The utility model is further improved in that: the inner wall of the detonation section of the combustion chamber is provided with a first helical obstacle, the inner wall of the detonation section of the combustion chamber is provided with a second helical obstacle, and the pitch of the first helical obstacle is less than The pitch of the second helical obstacle.

Compared with the prior art, the utility model is a high-frequency pulse detonation combustion power device. In addition to designing a fuel nozzle on the head of the combustion chamber, multiple nozzles are designed at equal intervals between the detonation section and the detonation section of the combustion chamber. Auxiliary fuel nozzles divide the combustion chamber into multiple small areas, and each nozzle is responsible for the fuel supply of one area, which can reduce the filling time of the combustion chamber, increase the operating frequency of the engine, and increase the thrust generated by the engine per unit time; in addition, in The tail of the pulse detonation combustion chamber is designed with a multi-stage serial booster structure, which can further increase the thrust of the engine.

Furthermore, because the detonation wave strengthening structure of the helical obstacle in the combustion chamber adopts a variable pitch design, the DDT distance for the transition from deflagration to detonation in the combustion chamber can be shortened on the premise of reducing the flow resistance of the engine combustion chamber.

【Description of drawings】

Fig. 1 is the overall structure diagram of a kind of high-frequency pulse detonation combustion power device of the present utility model;

Fig. 2 is a schematic diagram showing the structure of the multi-stage serial boosting booster of the power plant shown in Fig. 1;

Fig. 3 is a view along the line A-A of Fig. 2 .

Among them: 1. Air pipeline of main nozzle; 2. Fuel pipeline of main nozzle; 3. Main nozzle; 4. End cover of combustion chamber head; 5. Pulse detonation combustion chamber; 6. Spark plug; 7. Ignition section of combustion chamber ; 8. Auxiliary nozzle fuel pipeline; 9. Auxiliary nozzle air pipeline; 10. Detonation section of combustion chamber; 11. First spiral obstacle; Chamber detonation section; 15. Multi-stage series boosting structure support plate; 16. Multi-stage series boosting structure connecting rod; 17. Tail nozzle; 18. Multi-stage series boosting structure; 19. Gas flow path; 20. The first arc-shaped intake end face; 21. The first axisymmetric direct injection pipe; 22. The first-stage booster; 23. The support plate of the first inter-stage booster; 24. The connecting rod of the first inter-stage booster; 25. The second arc-shaped intake end face; 26. The second axisymmetric direct injection pipe; 27. The second-stage booster; 28. The support plate of the second inter-stage booster; 29. The second inter-stage booster connection Rod; 30, the third arc-shaped air intake end face; 31, the third axisymmetric direct injection pipe; 32, three-stage booster.

【Detailed ways】

The specific embodiments of the utility model will be described in detail below in conjunction with the accompanying drawings.

Referring to Fig. 1 to Fig. 3, the utility model is a high-frequency pulse detonation combustion power device, which includes a pulse detonation combustion chamber 5, a tail nozzle 17 and a multi-stage serial booster structure 18 connected in sequence from left to right.

Wherein, the pulse detonation combustor 5 comprises a combustor head end cover 4, a combustor ignition section 7, a combustor detonation section 10 and a combustor detonation section 14 connected successively from left to right, and the combustor detonation section 14 The right end is connected with the tail nozzle 17; the combustion chamber head end cover 4 is provided with a main nozzle 3, and the main nozzle 3 is provided with a main nozzle air pipeline 1 and a main nozzle fuel pipeline 2; A spark plug 6 is provided; a number of auxiliary nozzles 12 are arranged at equal intervals in the circumferential direction of the combustion chamber detonation section 10 and the combustion chamber detonation section 14 along the axial direction, and the auxiliary nozzle 12 is provided with an auxiliary nozzle air pipeline 9 and an auxiliary nozzle fuel pipeline. 8. In this way, the main nozzle 3 and the auxiliary nozzle 12 can fill the combustion chamber at the same time, so that each nozzle only needs to be responsible for the fuel supply of a small space in the combustion chamber, which can reduce the filling time of the combustion chamber and increase the operating frequency of the engine.

Further, the tail nozzle 17 is a converging nozzle with a contraction ratio of 1.2 to 1.5 and a convergence angle of 6 to 10 degrees. The inner wall of the detonation section 10 of the combustion chamber is provided with a first helical obstacle 11, and the inner wall of the detonation section 14 of the combustion chamber is provided with a second helical obstacle 13, and the pitch of the first helical obstacle 11 is smaller than the second The pitch of the helical obstacle 13. Since the smaller the pitch of the obstacle-reinforced structure, the greater the turbulence of the combustible mixture in the combustion chamber, and the stronger the heat exchange intensity between the airflows, so the transition distance DDT from deflagration to detonation can be shortened, but the smaller the pitch, the inner flow resistance of the engine The larger the pitch, the DDT distance can be shortened while reducing the flow resistance of the engine after adopting the variable pitch design.

Referring to FIG. 2 and FIG. 3 , the multi-stage series booster structure 18 includes a first-stage booster 22 , a second-stage booster 27 and a third-stage booster 32 connected in sequence from left to right. Wherein, the first-stage booster 22 includes a first arc-shaped intake end surface 20 and a first axisymmetric direct injection pipe 21, and the second-stage booster 27 includes a second arc-shaped intake end surface 25 and a second axisymmetric direct injection pipe. 26. The three-stage booster 32 includes a third arc-shaped intake end face 30 and a third axisymmetric direct injection pipe 31; Circumferentially, one end of the four multi-stage series booster structure support plates 15 is connected with the corresponding multi-stage series booster structure connecting rod 16, and the other end is connected with the tail of the pulse detonation combustion chamber 5; The pusher connecting rods 24 are evenly arranged in the circumferential direction of the second arc-shaped intake end face 25, and one end of the four first interstage booster support plates 23 is connected with the corresponding first interstage booster connecting rods 24, and The other end is connected with the first axisymmetric direct injection pipe 21; the four second interstage booster connecting rods 29 are evenly arranged in the circumferential direction of the third arc-shaped intake end surface 30, and the four second interstage booster support One end of the plate 28 is connected with the corresponding second interstage booster connecting rod 29 , and the other end is connected with the second axisymmetric direct injection pipe 26 .

When the high-speed pulse detonation gas is discharged from the tail nozzle 17 and enters the first-stage booster 22, due to the effect of the viscous force of the air flow, the air upstream of the arc-shaped intake end face 20 will inevitably be sucked into the engine, resulting in air upstream of the arc-shaped intake end face 20 The dynamic pressure of the total pressure increases and the static pressure decreases, while the static pressure of the air downstream of the arc-shaped inlet end face 20 remains unchanged, which must generate additional thrust at the arc-shaped inlet end face 20 due to the pressure difference. Wherein, the direction of the arrow is the gas flow path 19 .

In order to further understand the utility model, the utility model is further described in conjunction with specific embodiments now.

The utility model is a high-frequency pulse detonation combustion power device, which comprises a pulse detonation combustion chamber 5, a tail nozzle 17 and a multi-stage serial boosting structure 18. The pulse detonation combustion chamber 5 is mainly composed of the combustion chamber head end cover 4, the combustion chamber ignition section 7, the combustion chamber detonation section 10 and the combustion chamber detonation section 14. In the present embodiment, the combustion chamber diameter is 60mm and the length is 1300mm; The chamber head end cover 4 is located at the forefront of this embodiment, and the main nozzle 3 is installed at its central position; the combustion chamber ignition section 7 is located downstream of the combustion chamber head end cover 4, and is 300 mm long. The spark plug 6 for ignition is installed in the middle of the axial position; the ignition section 10 of the combustion chamber is located downstream of the ignition section 7 of the combustion chamber, and is 400mm long, and a first spiral obstacle with a pitch of 50mm and a diameter of 8mm is arranged inside it. 11; The detonation section 14 of the combustion chamber is located downstream of the detonation section 10 of the combustion chamber point, and is 600 mm long, and is equipped with a second spiral obstacle 13 with a pitch of 80 mm and a diameter of 8 mm; Seven auxiliary nozzles 12 are designed at equal intervals in the axial position of the detonation section 14, and the distance between each auxiliary nozzle 12 is 120mm; the tail nozzle 17 is located downstream of the detonation section of the combustion chamber, the contraction ratio is 1.5, and the convergence angle is 6 degrees The multi-stage series boosting structure 18 is coaxially arranged in the tail nozzle 17 downstream of the combustion chamber, and the four multi-stage series boosting structure support plates 15 and the multi-stage series boosting structure struts 15 which are uniformly arranged in the circumferential direction of the tail of the combustion chamber detonation section 14 are arranged coaxially with the combustion chamber. The push structure connecting rod 16 forms an integral body with the pulse detonation combustion chamber 5 .

This embodiment can be used for both air-breathing pulse detonation engines and rocket-type pulse detonation engines. The working process of the high-frequency pulse detonation combustion power device in this embodiment is: open the air and fuel pipelines of the main nozzle 3 and each auxiliary nozzle 12, quickly fill the pulse detonation combustion chamber 5 with fuel, and close the fuel after the fuel filling is completed. The air and fuel pipelines of the main nozzle 3 and each auxiliary nozzle 12 are simultaneously ignited by the spark plug 6 to ignite the combustible mixed gas in the combustion chamber, forming a deflagration wave in the ignition section 7 of the combustion chamber, and the deflagration wave passes through the small-pitch helical obstacle in the detonation section 10 of the combustion chamber After the material 11 is intensified, it gradually turns into a detonation wave, which is further strengthened by the second spiral obstacle 13 in the detonation section 14 of the combustion chamber, and then is accelerated and discharged from the tail nozzle 17. Under the action of the viscous force of the air flow, the The detonation gas drives the air around the tail nozzle 17 to be sucked into the engine, causing a static pressure difference to form at the arc-shaped intake end face 20 of the first-stage booster 22, thereby generating additional thrust. After passing through the first-stage booster 22, the high-speed gas further Drive the air upstream of the arc-shaped intake end faces of the second-stage booster 27 and the third-stage booster 32 to enter the engine, and generate additional thrust at the arc-shaped intake end faces of the booster structures of each stage, and finally the gas is discharged from the third-stage booster. The axisymmetric direct injection pipe 31 of the pusher 32 is discharged to the atmosphere. After the detonation gas is completely discharged from the engine, the main nozzle 3 and the main nozzle air pipeline 1 and the auxiliary nozzle air pipeline 9 of each auxiliary nozzle 12 are opened. Fill and blow out the isolation gas in the shock chamber, then open the main nozzle fuel pipeline 2 and the auxiliary nozzle fuel pipeline 8 of the main nozzle 3 and each auxiliary nozzle 12, and start a new round of fuel filling of the pulse detonation combustion chamber, and repeat the cycle like this Work. Because this embodiment uses 8 fuel nozzles, compared with the traditional pulse detonation engine that only uses one nozzle at the head of the combustion chamber, the operating frequency of the engine in this embodiment can be increased by at least seven times.

Claims (6)

1. A high-frequency pulse detonation combustion power device is characterized in that: the device comprises a pulse detonation combustion chamber (5), a tail nozzle (17) and a multi-stage series boosting structure (18) which are sequentially connected from left to right; wherein,

the pulse detonation combustor (5) comprises a combustor head end cover (4), a combustor ignition section (7), a combustor detonation section (10) and a combustor detonation section (14) which are sequentially connected from left to right, and the right end of the combustor detonation section (14) is connected with a tail nozzle (17); a main nozzle (3) is arranged on the head end cover (4) of the combustion chamber, and a main nozzle air pipeline (1) and a main nozzle fuel pipeline (2) are arranged on the main nozzle (3); spark plugs (6) are arranged on the circumferential direction of the ignition section (7) of the combustion chamber; a plurality of auxiliary nozzles (12) are arranged on the circumferential direction of the combustion chamber detonation section (10) and the combustion chamber detonation section (14) at equal intervals along the axial direction, and an auxiliary nozzle air pipeline (9) and an auxiliary nozzle fuel pipeline (8) are arranged on each auxiliary nozzle (12).

2. The high frequency pulse detonation combustion power plant of claim 1, characterized by: the tail nozzle (17) is a convergent nozzle, the contraction ratio is 1.2 to 1.5, and the convergence angle is 6 to 10 degrees.

3. The high frequency pulse detonation combustion power plant of claim 1, characterized by: the multistage series thrust augmentation structure (18) comprises a first-stage thrust augmentation device (22), a second-stage thrust augmentation device (27) and a third-stage thrust augmentation device (32) which are sequentially connected from left to right.

4. The high frequency pulse detonation combustion power plant of claim 3, characterized by: the first-stage thrust booster (22) comprises a first arc-shaped air inlet end face (20) and a first axisymmetric straight nozzle (21), the second-stage thrust booster (27) comprises a second arc-shaped air inlet end face (25) and a second axisymmetric straight nozzle (26), and the third-stage thrust booster (32) comprises a third arc-shaped air inlet end face (30) and a third axisymmetric straight nozzle (31); a plurality of multistage series-connection boosting structure connecting rods (16) are uniformly arranged in the circumferential direction of the first arc-shaped air inlet end face (20), one end of each multistage series-connection boosting structure supporting plate (15) is connected with the corresponding multistage series-connection boosting structure connecting rod (16), and the other end of each multistage series-connection boosting structure supporting plate is connected with the tail of the pulse detonation combustion chamber (5); a plurality of first-stage thrust increaser connecting rods (24) are uniformly arranged in the circumferential direction of the second arc-shaped air inlet end surface (25), one ends of a plurality of first-stage thrust increaser supporting plates (23) are connected with the corresponding first-stage thrust increaser connecting rods (24), and the other ends of the first-stage thrust increaser supporting plates are connected with the first axisymmetric straight spray pipe (21); a plurality of second-stage thrust increaser connecting rods (29) are uniformly arranged in the circumferential direction of the third arc-shaped air inlet end surface (30), one ends of a plurality of second-stage thrust increaser supporting plates (28) are connected with the corresponding second-stage thrust increaser connecting rods (29), and the other ends of the second-stage thrust increaser connecting plates are connected with the second axisymmetric straight spray pipe (26).

5. The high frequency pulse detonation combustion power plant of claim 4, characterized in that: the number of the multistage series thrust augmentation structure support plate (15) and the number of the multistage series thrust augmentation structure connecting rods (16) are both 4, the number of the first-stage thrust augmentation support plate (23) and the first-stage thrust augmentation connecting rods (24) is both 4, and the number of the second-stage thrust augmentation support plate (28) and the second-stage thrust augmentation connecting rods (29) is both 4.

6. The high frequency pulse detonation combustion power plant of any one of claims 1 to 5, characterized by: the inner wall of the combustion chamber detonation section (10) is provided with a first spiral obstacle (11), the inner wall of the combustion chamber detonation section (14) is provided with a second spiral obstacle (13), and the pitch of the first spiral obstacle (11) is smaller than that of the second spiral obstacle (13).