Jet single-point impact compression combustion engine and lifting-body aircraft

Abstract

The invention provides a jet single-point impact compression combustion engine which comprises a combustion chamber and is characterized in that the end surface of the air inlet end of the combustionchamber is uniformly provided with multiple propellant spray holes in a circumferential direction; center lines of extension lines of the propellant spray holes are commonly intersected at an A pointin a center line of the combustion chamber; the inlet end of the combustion chamber is provided with inlet valves for controlling flow rates of the corresponding propellant spray holes, and the outletend is provided with outlet valves; the inlet valves and the outlet valves are alternately opened and closed; and after the inlet valves are closed, the outlet valves are opened after a delay time t.For the engine, a detonation reaction may be generated in the combustion chamber, and high heat is instantaneously released, is quickly absorbed and utilized and converted into a thrust, so that exhaust gas is discharged into a surrounding environment, and the thermal efficiency of the engine is improved; and an axisymmetric aircraft and a lifting-body aircraft adopting the engine are large in flight thrust as well as small in noise and vibration.

Description

technical field [0001] The invention relates to a jet single-point impact compression combustion engine, an axisymmetric aircraft and a lifting body aircraft, and belongs to the technical field of aircraft. Background technique [0002] Liquid rocket engine combustion is based on physical processes such as multi-jet collision, atomization, ignition (self-ignition), but its purpose is combustion or deflagration, and the collision points are many and scattered. Even with a closed cycle, the thermal efficiency of the engine is still low, and the engine discharges a large amount of waste heat. [0003] Equally, the various types of engines that aerospace vehicles have used at present, including piston type, turbojet (or fan) type, ram air-breathing type, combined cycle type, etc., thermal efficiency is generally not high, wasted quite a lot of energy, and polluted environment. Most of the engine cycle mode is relatively simple, such as constant pressure combustion, constant vo...

AI Technical Summary

Problems solved by technology

[0003] Equally, the various types of engines that aerospace vehicles have used at present, including piston type, turbojet (or fan) type, ram air-breathing type, combined cycle type, etc., thermal efficiency is generally not high, wasted quite a lot of energy, and polluted surroundings

Most of the engine cycle mode is relatively simple, such as constant pressure combustion, constant volume combustion, etc., and the adaptability to different heights and speeds is limited

Combined cycle engines are emerging, but the structure and control of combined cycle engines are complex

[0004] The thermal efficiency of pulse detonation engine is high, but the noise and vibration of detonation combustion are relatively large, which objectively hinders the research and development of this technology

Images