Abstract
Injecting water in the mixing layer of rocket motor jets is a means to reduce jet noise. The calculation of the sound pressure signals at the prescribed receivers was performed by FW-H acoustics model under the condition of water injection and without water injection. The calculation results show that the jet noise is with obvious directivity. The total sound pressure levels are obviously much higher in 10° to 30° direction than that in other direction. The sound pressure levels at the condition of water injected are lower than that of without water injection at the all receiver points, which indicates that water injection can reduce jet noise effectively.
Highlights
When Rocket engine is at work, Propellant combusting in chamber generates high temperature and high pressure combustion gas
The solid curve shows the total sound pressure level change with the azimuth angle induced by jet flow field at the condition without water injection, while the dotted line shows that induced by jet flow field with water injection
1) Under the same initial conditions, the highest temperature of flow field at downstream of the nozzle exit is less than 1300 k after water was injected
Summary
When Rocket engine is at work, Propellant combusting in chamber generates high temperature and high pressure combustion gas. It will produce violent jet noise to the surrounding. Experimental and numerical study on the water injection to reduce noise are carried out. The numerical calculation is based on the equivalent jet parameter method to estimate the size of the noise. CFD method will be applied to calculate the near field flow field and sound source, combined with the method of solving the wave equation and the far field acoustic field distribution, to research rocket engine jet flow and gas dynamic field noise characteristics, and calculate the. Effect of water injection on jet flow field and sound field. It provides numerical reference for water injection to reduce noise of the rocket engine
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