Abstract
As a efficient and simple design, expander cycle is widely applied in LRE engineering, but it is seldomly used on scramjet research. In order to establish a complete mathematical model for expander cycle scramjet, a control-oriented model for expander cycle scramjet is proposed in this paper. This model consists of four major parts: combustor, cooling channel, turbo pump and nozzle and gives the result of pressure, temperature, mach number and velocity distribution of combustor and cooling channel and is capable of simulate both pure supersonic combustion mode and supersonic shock wave mode of the combustor. Each part is given by specific mathematical description, which contains the calculation of airflow, combustion, heat transfer and thermal cracking of kerosene. By putting all these parts together, a complete model is formed. This model is proposed to calculate the performance and condition of the engine precisely, comprehensively, swiftly and can be directly used in further study.
Highlights
Hypersonic airbreathing vehicle has shown its bright future in both military and civil uses
We test the model by setting the boundary conditions with the mach number of 2.7, the temperature of 1160K, the pressure of 0.1MPa
The scramjet should be working under supersonic shock wave mode, according to equation 17
Summary
Hypersonic airbreathing vehicle has shown its bright future in both military and civil uses. The working process of expander cycle scramjet is shown in fig.. Hot fuel powers the turbine to drive the centrifugal pump. After flow out of the turbine, the fuel is injected into the combustor to mix with air and release heat after combustion. In this paper, aiming on forming a self-holding system that contains the key factors of a kerosene based scramjet, a quasi-one dimensional model for expander cycle scramjet is proposed. This model can be used on analysis the working characteristics and predict the performance of expander cycle scramjet
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