Patent ID: 6220016
Filing Date: 2001-04-24
Classification: F02K,F05D

Abstract:
A rocket engine, comprising:a. a first combustion chamber comprisingi. an outlet; andii. a first combustion chamber liner comprising at least one first orifice; andb. a first annular passage at least partially surrounding said first combustion chamber liner;c. a second combustion chamber in fluid communication with said outlet of said first combustion chamber, wherein said second combustion chamber comprises a second combustion chamber liner comprising at least one second orifice; andd. a second annular passage at least partially surrounding said second combustion chamber liner, wherein said second annular passage is in fluid communication with said first annular passage, whereby when operating, said first combustion chamber generates an effluent, a first portion of said effluent is discharged through said at least one first orifice, through said first and second annular passages, through said at least one second orifice, and into said second combustion chamber so as to provide for effusion cooling of said second combustion chamber liner.