Patent ID: 6050085
Filing Date: 2000-04-18
Classification: F02K,F05D,F23C,F23D

Abstract:
A method of injecting a first and a second fuel component into a combustion chamber of a rocket engine, comprising the steps of:injecting the first and the second fuel components jointly into the combustion chamber by means of one or more injection elements, wherein one injection element guides the first fuel component in an inner cylindrical stream and allows it to flow out in such a cylindrical stream into a mixing zone, and wherein the injection element guides the second fuel component in an annular stream surrounding the inner cylindrical stream and allows it to flow out in such an annular stream into the mixing zone, andguiding in the injection element the first and/or the second fuel component through a turbulence grid which produces turbulence over an entire stream cross-section in order to achieve a good intermixing of the two fuel components in the mixing zone, wherein the turbulence grid produces a pressure drop and wherein the energy released during the pressure drop is at least partially converted into turbulence energy of the stream of the first and/or the second fuel component.