An internal/external compression integrated adjustable variable geometry intake port and its design method

Abstract

The invention discloses an internal and external compression integrated regulating type variable-geometry gas inlet path. A compression surface capable of rotating around a shaft is designed on the basis of a supersonic-speed gas inlet path structure, and a deflection position of the compression surface can be regulated according to a flight condition; and simple realizability of a variable-geometry mechanism during practical engineering application is taken into consideration while incoming-flow Mach number range of the gas inlet path is expanded and pneumatic performance of the gas inlet path is improved. The invention further provides a design method of the gas inlet path.

Description

technical field [0001] The invention belongs to the technical field of engines, and in particular relates to a supersonic variable-geometry intake port and a design method thereof. Background technique [0002] Because of its simple structure and high thrust, the ramjet is widely used as a high-performance propulsion device for supersonic aircraft. As one of the key aerodynamic components of the ramjet, the supersonic inlet directly affects the overall performance of the propulsion system and even the entire aircraft. For a supersonic inlet operating in a wide range of Mach numbers, it is required that the inlet not only have self-starting capability at a lower flight Mach number, but also have a higher flow coefficient and total pressure in a wide range. recovery and anti-backpressure capabilities, the conventional geometric inlet can no longer meet the requirements for further improvement of engine performance in a wide range of Mach numbers. A natural choice for airway ...

AI Technical Summary

Problems solved by technology

However, the rotation of the lip cover will significantly increase the external resistance of the aircraft, and the resulting aircraft trim problem is difficult to be effectively solved. Although the variable-geometry inlet designed by Sanders achieves relatively excellent performance in theory, it is complicated. The control mechanism makes it difficult to guarantee the coordination and continuity of the actual operation

[0004] Undoubtedly, optimizing the variable geometry profile through the adjustment mechanism to realize the rotation and expansion of the lip and the rotation of the compression surface can significantly improve the aerodynamic performance of the inlet in a wide range of Mach numbers. However, if the control means of the mechanical adjustment mechanism are too complicated, Too many moving parts will reduce the feasibility of its practical application

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