Low-cost closed type pulse detonation wind source engine

Abstract

The invention discloses a low-cost closed type pulse detonation wind source engine, which belongs to the technical field of gas engines, and comprises a combustion explosion chamber, a detonation chamber and a composite flow guide pipe, the two sides of the detonation chamber are respectively provided with the combustion explosion chamber and the composite flow guide pipe, one end of the combustion explosion chamber far away from the detonation chamber is provided with a fuel nozzle, and the other end of the combustion explosion chamber is provided with an air inlet. Nitrogen inlets are formed in the outer side wall of the combustion and explosion chamber and the outer side wall of the detonation chamber respectively, an igniter is arranged on the outer side wall of the combustion and explosion chamber, and a vortex air inlet is formed in the outer side wall of the composite flow guide pipe and used for eliminating turbulent flow generated in the detonation process of gas exhausted after ignition and explosion of fuel. The airflow is output more stably under the action of vortex air, and continuous high-speed wind energy output is formed.

Description

technical field [0001] The invention relates to the technical field of gas engines, in particular to a low-cost closed pulse detonation air source engine. Background technique [0002] The detonation engine that is common at home and abroad at present, its purpose is basically as the flight power device of aircraft, basically does not have the wind source equipment application research and mature commodity that can be applicable to wind tunnel. And on the structural type of all types of detonation engines, the detonation chamber is all open to the outlet, which leads to low ignition efficiency and serious waste of fuel in the existing detonation engines. [0003] In the existing detonation engine model, after a detonation ignition process ends, in order to prevent the new fuel from entering the detonation chamber from being misfired by the unburned residual fire, there is generally a scavenging process, and this scavenging process will Occupies the ignition time and frequen...

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Problems solved by technology

[0002] At present, the common detonation engine at home and abroad is basically used as the flight power device of the aircraft, and there is basically no application research and mature products of wind source equipment suitable for wind tunnels.

And on the structural type of all types of detonation engines, the detonation chamber to the outlet are all open types, which leads to low ignition efficiency and serious fuel waste of existing detonation engines

[0003] In the existing detonation engine model, after a detonation ignition process ends, in order to prevent the new fuel from entering the detonation chamber from being misfired by the unburned residual fire, there is generally a scavenging process, and this scavenging process will Occupies the ignition time and frequency of the engine, reduces the output power and thrust-to-weight ratio of the engine, and at the same time increases the difficulty of the engine control system and increases the difficulty of structural design; during the design of small guided missiles and aircraft rudder shape parameters and flight tests, it is often necessary to carry out Simulate the flight environment test to obtain the best shape design parameters and control performance requirements that meet the aerodynamic requirements; while the general wind tunnel test device, the cost of the wind source generation process is extremely high, and involves a wind tunnel equipment system that generates high-speed wind sources Complexity and serious energy consumption; generally speaking, the construction cost of this kind of wind tunnel test device is also very high, especially the wind tunnel technology that reaches subsonic or supersonic wind speed is more complicated; while conventional commercial wind tunnel test equipment, its The maximum wind speed generally can only reach a wind speed of about 50 m / s, and it cannot be used as a wind source for the aerodynamic test of the projectile at all.

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