Patent ID: 6189315
Filing Date: 2001-02-20
Classification: F02K

Abstract:
A gas generator and ignitor assembly for generating a pressurized hot gas for driving a turbopump of a rocket engine, said assembly comprising: an injector and a combustion chamber, said injector having a body member including a fuel inlet port opening into a fuel passageway and an oxidizer inlet port opening into an oxidizer passageway, five substantially concentric annular grooves formed within said body member opening outwardly to the exterior of the body member and disposed about an axis extending through said body member, the annular groove closest to said axis, the annular groove furthest from said axis and one of the annular grooves between these grooves communicating with said fuel passageway for receiving fuel therefrom, the remainder of said five annular grooves communicating with said oxidizer passageway for receiving oxidizer therefrom, a plate secured to said body member substantially normal to said axis for closing said five grooves from the exterior of said body member, an array of bores arranged in sets of three radially spaced apart circular rows about said axis formed in said plate, each bore in one row being aligned with a bore in each of the other two rows of each set to form a triplet of bores, a first of the bores of each triplet being in the row furthest from said axis and a second of the bores being in the row closest to said axis communicating with a fuel receiving an annular groove, and the third of the bores being in the other row communicating with an oxidizer receiving annular groove, said combustion chamber comprising a conduit having a mixing and ignition section and an exhaust section secured to said injector with said mixing and ignition section communicating with and receiving fuel and oxidizer from said bores.