Liquid Mixing Engine Combustion And Burning Rate Characteristics

Hybrid rocket motors keep the features of low cost,high reliability,and no hazards.In recent years, there has been a resurgence of interest in the development of hybrid rocket engines for advanced launch vehicle applications. But in hybrid rocket motors,the combustion efficiency and regression rate are very slow.lt is important to study the combustion processes and the performance of regression rate in hybrid rocket motors.Of particular importance in the design of hybrid rocket motors is the fuel surface regression rate and the manner in which it varies with operation conditions. In this paper,hybrid combustion is studied and a model of hybrid combustion is presented.The paper summarizes and discusses different types of regression rate models that have been developed by several researchers during previous investigations of hybrid combustion.These analyzes are useful in guiding the development of a hybrid rocket motor.In this paper,simple reacting flow model of hybrid rocket motor based on Arrenius formula and Eddy Break-Up model is established and used to simulate an experimental motor. The paper also discusses size scale-up studies of hybrid rocket motors and the numerical simulation of two-phase hybrid combustion. With computations and analysis, the comprehension on the combustion process and knowledge about the performance of regression rate are increased, and some significative results are listed below:1. Regression rate varies greatly along x axis. 2. The combustion efficiency of hybrid rocket motor is very low.In order to increase combustion efficiency,we can use vaporization chamber and mixing chamber. 3.Regression rate decreases as the port dimension is increased.The paper also makes a whole design of experimental hybrid rocket motor system,and discusses the result of motor firing.