This liquid propellant engine is a experimental rocket engine. The initial idea was only use standard parts and standard materials for the manufacturing the A-1 enegine. This task was hard since these types of engines have the work conditions more critical than the quotidian materials.
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3D view of the A-1 liquid propellant rocket engine.
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Here are the specs for the regenerative cooled engine. The design is still in progress so these are subject to change:
Fuel: Liquid Kerosene
Oxidizer: Gas Oxygen
Mixture ratio: 2
Thrust: 1,000 N (225 lbf)
Chamber pressure: 20.7 Bar (300 psia)
Chamber diameter: 50mm (1.97 inches)
Chamber length: 137 mm ( 5.39 inches)
Nozzle throat diameter: 20 mm ( 0.79 inches)
Nozzle exit diameter: 52mm ( 2.05 inches)
Injector pairs: 4 units of the triplet type
Fuel injection diameter: 1 mm (0.039 inches)
Oxidizer injector diameter: 5 mm (0.197 inches)
Chamber temperature:3,245 Deg. Cº( 6,333 Deg. Rº, 5873 Deg. Fº)
Chamber material: Copper alloy
Regenerative cooling system:
http://en.wikipedia.org/wiki/Regenerative_cooling_(rocket)
