A 6 in. diameter ablative combustion chamber has been designed for use in evaluation tests on rocket engine components. This combustion chamber was designed for operation at 1000 psia chamber pressure with the propellant combination N2O4 and 50% N2H4 - 50% UDMH at a mixture ratio of 2.1/1. This report presents the design and fabrication of two complete combustion chamber assemblies and two spare combustion chamber liners. (Author)
The Design and Manufacture of a 6 Inch Diameter Ablative Combustion Chamber
1965
26 pages
Report
Keine Angabe
Englisch
Combustion & Ignition , Combustion chambers , Manufacturing , Rocket engines , Rocket components , Design , Operation , Liquid rocket propellants , Nitrogen compounds , Tetroxides , Hydrazine , Dimethyl hydrazine (1-1) , Instrumentation , Heat transfer , Specifications , Thermal analysis , Thermal stresses