Patent ID: 6269647
Filing Date: 2001-08-07
Classification: F02K,F05D

Abstract:
A rotor system for a rocket engine, comprising:a. a first hollow shaft portion having an axis of rotation, wherein a first end of said first hollow shaft portion is adapted to receive a first fluid propellant component;b. at least one first rotary orifice operatively coupled to said first hollow shaft portion, wherein said at least one first rotary orifice is in fluid communication with an interior of said first hollow shaft portion;c. an annular duct surrounding at least a portion of said first hollow shaft portion, wherein a first end of said annular duct is adapted to receive a second fluid propellant component;d. at least one second rotary orifice operatively coupled to said first hollow shaft portion, wherein said at least one second rotary orifice is in fluid communication with said annular duct;e. a second hollow shaft portion, wherein a first end of said second hollow shaft portion is operatively coupled to a second end of said first hollow shaft portion, and an interior of said second hollow shaft portion is in fluid communication with said interior of said first hollow shaft portion; andf. at least one third rotary orifice, wherein said at least one third rotary orifice is in fluid communication with said interior of said second hollow shaft portion.