Abstract
Based on relative theories of gas dynamics and computational fluid dynamics, the flow field computation software ANSYS Fluent was used to simulate the steady flow field of the solid type ignition device of liquid-propellant rocket engine in two working conditions (condition I: without ignition channel, condition II: with ignition channel). On this basis, the influence of ignition channel on the working characteristics of the solid type ignition device of the liquid-propellant rocket engine was analyzed and experimentally tested. The results showed that when the pressure in the combustion chamber was atmospheric pressure, under condition II, the gas velocity at the throat of the ignition device did not reach the sonic velocity, and the position of sonic velocity moved to the downstream section of the ignition channel. Compared to condition I, the gas velocity and energy at the ignition outlet increased, which would be beneficial for initial ignition, and the gas pressure and temperature at the throat increased as well, indicating that the structural strength at the throat should be evaluated. The gas flow, gas pressure, and gas temperature at the ignition outlet decreased compared to working condition I, yet the changes were small and would have minimal effect on the ignition performance. During the pressure increase process in the combustion chamber, the gas pressure, velocity, temperature, flow, and energy at the ignition outlet experienced a steady stage in both working conditions before coming to an inflection point. The inflection point under condition II is smaller than that under condition I. To improve the ignition reliability, the working pressure of the ignition device should be further increased.
Highlights
For a solid type ignition device of a liquid-propellant rocket engine, normal ignition of the engine is achieved by providing power to the igniter, which ignites the ignition powder and the main propellant grain in the ignition device, thereby producing high-temperature gas which is injected into the cavity of the main combustion chamber of the thrust chamber to ignite the propellant
The results showed that when the pressure in the combustion chamber was atmospheric pressure, under condition II, the gas velocity at the throat of the ignition device did not reach the sonic velocity, and the position of sonic velocity moved to the downstream section of the ignition channel
When an ignition device is installed on a liquid-propellant engine, the configuration is constrained by the structure of the liquidpropellant engine such that the high-temperature gas released from the ignition device usually needs to pass through a relatively long ignition channel before it is introduced into the main combustion chamber, which affects the ignition performance of the ignition device
Summary
For a solid type ignition device of a liquid-propellant rocket engine (hereinafter referred to as an ignition device), normal ignition of the engine is achieved by providing power to the igniter, which ignites the ignition powder and the main propellant grain in the ignition device, thereby producing high-temperature gas which is injected into the cavity of the main combustion chamber of the thrust chamber to ignite the propellant. When an ignition device is installed on a liquid-propellant engine, the configuration is constrained by the structure of the liquidpropellant engine such that the high-temperature gas released from the ignition device usually needs to pass through a relatively long ignition channel before it is introduced into the main combustion chamber, which affects the ignition performance of the ignition device. It is of great theoretical and engineering value to carry out a numerical simulation and experimental study on gas transmission in narrow channels. The results of this study provide a basis for the optimal design of the ignition device of liquid-propellant engine
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