Thermal management system (TMS) design is considered to be a key technology for advanced aero engines and supersonic or hypersonic propulsion systems. In this paper, the concepts of coupling flow and thermodynamic networks are proposed for TMS design. In this method, the propulsion system is considered to be a zero-dimensional flow system. Components, subsystems and hence the entire engine system can be modelled using some basic flow and thermodynamics networks. The platform for TMS design, ThermalM, is developed based on this model. As an example, modelling for a Turbine Based Combined Cycle (TBCC) thermal management system is described. Performance of the fuel heat exchanger in the network is discussed in detail. With the TMS design technology, performance of the advanced propulsion system can be analysed.


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    Title :

    Integrated Thermal Management System Design for Advanced Propulsion System


    Contributors:
    Lou, De-Cang (author) / Guo, Wen (author) / Wang, Zhi-Guo (author) / Wang, Yong-Hong (author)


    Publication date :

    2012


    Size :

    7 Seiten





    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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