Rocket engine cooling system

Details Rocket engine cooling system Rocket engine cooling system

F - Mech Eng,Light,Heat,Weapons

02

K

F02K 9/64 (2006.01) F02K 9/60 (2006.01)

Patent

CA 2596260

A rocket engine has first and second combustion chambers, each having a liner at least partially surrounded by a respective annular passage. The annular passages are in fluid communication with each other such that a first portion of effluent generated by the first combustion chamber is directed through the first and second annular passages and into the second combustion chamber, thereby providing for effusion cooling of the second combustion chamber.

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