Heat transfer in porous media applied to liquid rocket engines

Kurzfassung

Advances in space propulsion require the use of new materials. The Institute of Space Propulsion at DLR Lampoldshausen (Germany) has been investigating for the application of porous materials in liquid rocket engines. The development of transpiration cooling for combustion chamber is based on such materials in a configuration where hydrogen flows through the wall. Another application is injector heads which offer a better homogenization of the propellants. The efficiency and reliability of such components depend on the permeability of the flow through the porous structure and the heat exchange between the fluid and the porous material. A description of those physical processes is necessary. A new experimental set up has been developed with requirements to reproduce and to control flow and heat transfer in a porous material at high temperature, high pressure and a wide range of mass flow. It gives the possibility to study the influence of the properties and the structure of the porous material, the properties of the fluid, the parameters of the flow and the heat loads. Appropriate measurements will be made in the fluid and on the material to determine the pressure loss and the thermal exchanges in the porous sample. The main objective is to develop appropriate models of permeability and heat transfer for real rocket components. This work presents the investigation made to develop such an experimental device. The design and the methodology of the measurements chosen are explained. First experimental results and CFD analysis are also given.

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