Combustion chamber structure, cooling channel structure and combustion system of scramjet engine

Abstract

The utility model discloses a scramjet engine combustion chamber structure, a cooling channel structure and a combustion system.The combustion chamber structure comprises a combustion chamber wall, a combustion chamber is defined by the combustion chamber wall, and a plurality of cooling channels are arranged in the combustion chamber wall at intervals in the circumferential direction of the combustion chamber wall; the extending direction of the cooling channel is consistent with the extending direction of the combustion chamber, the inner wall of the cooling channel is in a bamboo joint shape, the combustion system comprises a fuel chamber and the combustion chamber structure, and an outlet of the fuel chamber is connected with an inlet of the combustion chamber and an inlet of the cooling channel. An outlet of the cooling channel is connected with an inlet of the combustion chamber. According to the scramjet engine combustion chamber structure, the cooling channel structure and the combustion system, heat exchange between the cooling medium and the combustion chamber wall can be enhanced, the cooling effect is good, aviation fuel serves as the cooling medium of the combustion system, heat absorbed by the cooling medium can be further utilized, and the combustion efficiency in the combustion chamber is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of engine combustion chamber, provide a scramjet engine combustion chamber structure, cooling channel structure and combustion system especially. BACKGROUND

[0002] For scramjet engine, engine combustion chamber needs to bear the extremely high heat generated by supersonic speed combustion of fuel, and with the increase of the aircraft Mach number, the combustion chamber wall will face higher and higher temperature, which will affect the reliability of the engine, therefore, under the condition that the combustion chamber wall material does not change, how to enhance the convective heat transfer by changing the combustion chamber cooling channel structure to reduce the temperature of the combustion chamber wall becomes a problem to be solved. SUMMARY

[0003] In view of this, the utility model discloses a scramjet engine combustion chamber structure, cooling channel structure and combustion system to solve the problems existing in the prior art.

[0004] The utility model provides a scramjet engine combustion chamber structure on the one hand, including combustion chamber wall, the combustion chamber wall surrounds a combustion chamber, the inside of combustion chamber wall is along its circumferential interval and is provided with a plurality of cooling channels, the extension direction of cooling channel is identical with the extension direction of combustion chamber, and the inner wall of cooling channel is bamboo joint type.

[0005] Preferably, the convex part of the bamboo joint type inner wall of the adjacent cooling channels is correspondingly arranged, and the groove part of the bamboo joint type inner wall of the adjacent cooling channels is correspondingly arranged.

[0006] The utility model also provides a scramjet engine combustion chamber cooling channel structure, including a plurality of cooling channels that are arranged in the combustion chamber wall along the circumferential interval of the combustion chamber wall, the extension direction of cooling channel is identical with the extension direction of combustion chamber, and the inner wall of cooling channel is bamboo joint type.

[0007] Preferably, the convex part of the bamboo joint type inner wall of the adjacent cooling channels is correspondingly arranged, and the groove part of the bamboo joint type inner wall of the adjacent cooling channels is correspondingly arranged.

[0008] The utility model also provides a scramjet engine combustion system, including: fuel chamber and above-mentioned scramjet engine combustion chamber structure, wherein, the outlet of fuel chamber is connected with the inlet of combustion chamber and the inlet of cooling channel in the scramjet engine combustion chamber structure, and the outlet of cooling channel is connected with the inlet of combustion chamber.

[0009] The super-combustion ramjet engine combustion chamber structure provided by the utility model has the advantages of the cooling channel, in addition, the system uses aviation fuel as the cooling medium, the aviation fuel as the cooling medium can cool the combustion chamber wall and preheat and raise the temperature before entering the combustion chamber, and the combustion efficiency in the combustion chamber can be effectively improved.

[0010] The super-combustion ramjet engine combustion system provided by the utility model has the advantages of the cooling channel, in addition, the system uses aviation fuel as the cooling medium, the aviation fuel as the cooling medium can cool the combustion chamber wall and preheat and raise the temperature before entering the combustion chamber, and the combustion efficiency in the combustion chamber can be effectively improved. BRIEF DESCRIPTION OF DRAWINGS

[0011] The utility model will be explained further in detail in combination with the drawings and implementation:

[0012] Figure 1 The utility model provides the sectional view of the super-combustion ramjet engine combustion chamber structure;

[0013] Figure 2 The utility model provides the sectional view of the super-combustion ramjet engine combustion chamber structure; Figure 1 The utility model provides the sectional view of the super-combustion ramjet engine combustion chamber structure; DETAILED DESCRIPTION

[0014] The utility model will be explained further in detail in combination with the drawings and implementation:

[0015] In order to solve the problem that the temperature of the combustion chamber wall of the super-combustion ramjet engine is too high and the cooling effect is poor, as shown in Figure 1 、 Figure 2 The utility model provides a kind of super-combustion ramjet engine combustion chamber structure and its cooling channel structure, comprising: combustion chamber wall 1, the combustion chamber wall 1 is enclosed a combustion chamber 2, the inside of the combustion chamber wall 1 is spaced apart along its circumferential direction and is provided with multiple cooling channels 3, the extension direction of the cooling channel 3 is consistent with the extension direction of the combustion chamber 2, the inner wall of the cooling channel 3 is in bamboo joint type.

[0016] The super-combustion ramjet engine combustion chamber structure, by the inner wall of cooling channel design into bamboo joint type, so that the diameter of channel changes between gradually shrink or gradually expand, can increase the contact area of cooling medium and combustion chamber wall, also can promote the generation of turbulent flow, to strengthen the heat exchange of cooling medium and combustion wall, so that cooling medium can efficiently take away the heat of combustion chamber to combustion chamber wall, effectively reduce the temperature of combustion chamber wall, reach the effect of cooling.

[0017] As technical scheme improvement, as shown in Figure 2As shown, the protruding portions of the burl-type inner walls of the adjacent cooling channels 3 are arranged correspondingly, and the groove portions of the burl-type inner walls of the adjacent cooling channels 3 are arranged correspondingly.

[0018] The utility model discloses still provide a kind of hypersonic scramjet combustion chamber cooling channel structure, including the circumferential interval of combustion chamber wall 1 It is arranged in the multiple cooling channels 3 of combustion chamber wall 1, the extension direction of the cooling channel 3 is consistent with the extension direction of the combustion chamber 2, the inner wall of the cooling channel 3 is burl-type.

[0019] The cooling channel structure can increase the contact area of the cooling medium and the combustion chamber wall, and also can promote the generation of turbulent flow, thereby strengthening the heat exchange between the cooling medium and the combustion wall, so that the cooling medium can efficiently take away the heat from the combustion chamber to the combustion chamber wall, effectively reduce the temperature of the combustion chamber wall, and achieve the effect of cooling.

[0020] As an improvement of the technical scheme, as Figure 2 As shown, the protruding portions of the burl-type inner walls of the adjacent cooling channels 3 are arranged correspondingly, and the groove portions of the burl-type inner walls of the adjacent cooling channels 3 are arranged correspondingly.

[0021] The utility model discloses still provide a kind of hypersonic scramjet combustion system, it include: fuel chamber and above-mentioned hypersonic scramjet combustion chamber structure, wherein, the outlet of the fuel chamber is connected with the inlet of the combustion chamber 2 in the hypersonic scramjet combustion chamber structure and the inlet of cooling channel 3, the outlet of the cooling channel 3 is connected with the inlet of the combustion chamber 2.

[0022] The hypersonic scramjet combustion system has the advantages of the above-mentioned cooling channel. In addition, the system uses aviation fuel as the cooling medium. The aviation fuel as the cooling medium can not only cool the combustion chamber wall, but also preheat and warm up before entering the combustion chamber, which can effectively improve the combustion efficiency in the combustion chamber.

[0023] The specific embodiments of the utility model are written in a progressive manner, and the differences between the various embodiments are emphasized. The similar parts can be referred to each other.

[0024] The embodiments of the utility model are described in detail above in combination with the drawings, but the utility model is not limited to the above-mentioned embodiments. Within the knowledge range possessed by ordinary skilled persons in the art, various changes can be made without departing from the purpose of the utility model.

Claims

1. A scramjet engine combustion chamber structure, comprising a combustion chamber wall (1) forming a combustion chamber (2), characterized in that, The interior of the combustion chamber wall (1) is provided with a plurality of cooling channels (3) spaced circumferentially. The extending direction of the cooling channels (3) is consistent with the extending direction of the combustion chamber (2), and the inner wall of the cooling channels (3) is bamboo-shaped.

2. The scramjet engine combustion chamber structure according to claim 1, characterized in that: The protruding parts of the bamboo-shaped inner wall of the adjacent cooling channel (3) are correspondingly provided, and the grooved parts of the bamboo-shaped inner wall of the adjacent cooling channel (3) are correspondingly provided.

3. A cooling channel structure for the combustion chamber of a scramjet engine, characterized in that, It includes a plurality of cooling channels (3) arranged circumferentially within the combustion chamber wall (1), the extending direction of the cooling channels (3) being consistent with the extending direction of the combustion chamber (2), and the inner wall of the cooling channels (3) being bamboo-shaped.

4. The cooling channel structure for the combustion chamber of a scramjet engine according to claim 3, characterized in that: The protruding parts of the bamboo-shaped inner wall of the adjacent cooling channel (3) are correspondingly provided, and the grooved parts of the bamboo-shaped inner wall of the adjacent cooling channel (3) are correspondingly provided.

5. A scramjet engine combustion system, characterized in that, include: The fuel chamber and the scramjet engine combustion chamber structure according to any one of claims 1 or 2, wherein the outlet of the fuel chamber is connected to the inlet of the combustion chamber (2) and the inlet of the cooling channel (3) in the scramjet engine combustion chamber structure, and the outlet of the cooling channel (3) is connected to the inlet of the combustion chamber (2).

Images