Patent ID: 7690192
Filing Date: 2010-04-06
Classification: F02K

Abstract:
1. A rocket engine comprising: a combustor chamber; an inlet delivery duct coaxial with said combustion chamber; a plurality of liquid propellant injectors mounted to said inlet delivery duct; a swirl generator mounted to said inlet delivery duct, said swirl generator comprising a plurality of swirl vanes radially distributed within said inlet delivery duct and a flared bluffbody mounted to said plurality of swirl vanes to extend at least partially downstream of said plurality of liquid propellant injectors, at least one of said plurality of liquid propellant injectors are defined by said flared bluffbody; and a feed system to transport a liquid oxidizer and a liquid fuel, said feed system operable to convert either the liquid fuel or the liquid oxidizer to a gaseous state for communication upstream of said swirl generator, the other of said liquid oxidizer and said liquid fuel for communication to said liquid propellant injectors.