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  • Optimization of System Parameters for Gas-Generator Cycle Engine

    Paper number



    Dr. Xiao Y. Tong, Beijing University of Aeronautics and Astronautics, China



    The gas-generator cycle engine is a prime candidate for both booster and space engines because of its inherent simplicity, high reliability and technical maturity. In this cycle, the turbine flow-path is in parallel with the thrust chamber flow-path, and one turbine can drive one or two pumps. This paper built a generic system model for gas-generator cycle engine and optimized the engine system parameters. 
      This paper decomposed the gas generator cycle engine to several components such as thrust chamber, turbopump, gas generator, and so on. Numerical simulation codes were developed for each component and the system. According to different relationships of components, these modularized codes could be integrated arbitrarily via a graphical user interface. And chemical properties for the bipropellants types in the C-H-O-N system have been built into the simulation model.
      Based on the modularized engine system simulation code, a generic optimization procedure of gas-generator cycle system parameters was developed. According to the design mission, optimal engine system parameters could be decided for different components assembling forms by using this procedure. The optimization design variables were combustion chamber pressure and engine mixture-ratio, and the objectives were maximum engine specific impulse and maximum ratio of thrust to engine weight.
      One combined optimization algorithm, the genetic algorithm plus gradient-based algorithm was utilized during optimization procedure to increase the exploration globality. The concurrent distributed processing had also been included to save calculation time.
      Several multi-objective process methods such as e-constraint, Benson, goal programming, etc were used to obtain the design objectives’ pareto front. Comparative results were listed to show the impact of different methods on the design variables and objectives.
      The foregoing methods can also be used to optimize system parameters of other engine system.
    Abstract document


    Manuscript document

    IAC-05-C4.P.19.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.