A hypersonic intake layout for an annular combustor

Abstract

The invention discloses a hypersonic air intake layout for an annular combustion chamber, which includes: determining the diameter, length, and cone-to-column ratio of the aircraft to generate the profile of the aircraft; determining the capturing cross-sectional area of ​​the inlet to generate a reference flow field, and performing flow The initial inlet configuration is generated by line tracing; the initial inlet configuration is truncated at the throat position to obtain the configuration of the inlet; the dual inlet configuration is generated based on the configuration of the inlet, and the streamline The tracking method generates variable cross-section isolation sections to obtain the configuration of the air intake components; determines the bottom resistance surface of the steering gear bulge corresponding to each air intake component, and generates the outer surface of the air intake with the leading edge profile and bottom resistance surface of the air intake. rectify the surface, and install the steering gear and the rudder surface on the rectified surface outside the air inlet. The length of the inlet and isolation section can be greatly reduced, thereby reducing the viscous loss of the flow in the inner channel, and the boundary layer is swept by the shock wave, the flow field of the inlet and the isolation section is uniform, and the flow field quality is high. Strong anti-back pressure ability.

Description

technical field [0001] The invention relates to the technical field of intake port design, in particular to a hypersonic intake layout for an annular combustion chamber. Background technique [0002] Air-breathing hypersonic vehicle has huge military and civil potential because of its fast speed, long range and strong maneuverability. [0003] The air-breathing hypersonic vehicle faces the challenge of matching thrust and drag due to its fast flight speed and large flight resistance. Therefore, it is necessary to carry out the integrated design of the air inlet and the fuselage. The existing air-breathing hypersonic vehicle fuselage and air inlet integrated design are mainly divided into axisymmetric layout, lift body layout and waverider layout, which mainly use axisymmetric compression, two-dimensional compression intake and three-dimensional internal compression respectively. Switch to compressed intake form. [0004] The annular combustion chamber is mainly used in air...

AI Technical Summary

Problems solved by technology

[0008] Head air intake solution: The length of the engine internal flow channel of the head air intake solution is coupled with the length of the aircraft. The length of the engine internal flow channel needs to match the length of the aircraft, resulting in an excessively long internal flow channel and a large flow loss, thereby reducing engine performance or causing The engine cannot properly organize combustion;

[0009] Four-module X-type air intake scheme (two-dimensional air intake): This scheme can place the air intake on the body or tail of the aircraft, but because the boundary layer is thick, it must be designed with a partition that strips the boundary layer, resulting in structural weight Increased, increasing the difficulty of thermal protection

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