A schematic description of a rocket engine is given highlighting the needs of materials for such an application. The evolution of metallic materials from the HM7 engine used on the 3rd stage of Ariane 4, to the Vulcain engine for the central body of Ariane 5 is reviewed. The stresses of very low and very high temperatures as well as the particular environment (hydrogen-oxygen) are pointed out. The effect of the limitations of the metals on the rocket engine performance, principally in the maximal admissable temperature domain and the mass, are indicated. The advantages offered by ceramic matrix material composites with respect to maximal admissible temperatures and weight reduction are presented together with the gains hoped for with regard to the engine system. Three application domains are evoked divergent nozzles, combustion chambers, and the turbopump stators and turbines.
Evolution des Materiaux Utilises en Propulsion Fusee a Ergols Liquides (Evolution of Materials Used in Liquid Propellant Rocket Engines)
1991
11 pages
Report
No indication
English
Rocket Engines & Motors , Composite Materials , Engineering Materials , Ceramic matrix composites , Combustion chambers , Divergent nozzles , Liquid propellant rocket engines , Thermal resistance , Turbine pumps , Weight reduction , Ariane launch vehicle , Engine design , High temperature , Low temperature , Stators , Turbines , Foreign technology
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