Patent ID: 6082098
Filing Date: 2000-07-04
Classification: F02K

Abstract:
An ignition system for a rocket engine comprisingan ignitor,a faceplate having a centrally located ignitor port and first and second annular sections located radially outward of said port, said first annular section located radially inward of said second annular section, said ignitor mounted to said ignitor port,a plurality of first injector elements located in said first annular section of said faceplate and a plurality of second injector elements located in said second annular section, each of said injector elements having a first orifice defining a first flow area, and a second orifice defining a second flow area, said second orifice concentric with and radially outward of said first orifice relative to said first orifice and having a radially inner half and a radially outer half, said radially inner half located between said radially outer half and said ignitor port, each of said first injector elements located equidistant from said ignitor port, and,at least one insert located in the second orifice of one of said first injector elements, thereby reducing the second flow area of the second orifice in which said insert is located, wherein each of said inserts includes a semi cylindrical wall, and said insert is fixedly secured to said faceplate.