This program introduces novel mixing techniques for supersonic transport propulsion low emission combustor designs to dramatically reduce cost, weight and complexity and to improve performance. This innovation employs advanced multi-staged lobed mixers to very rapidly mix fuel and air, both temporally and spatially, with minimum momentum loss to the flows. In demonstrations for other applications, the concept has proven to improve the transition from air/air mixing to liquid/air mixing. This proposed work builds upon and extrapolates the existing body of knowledge to develop a predic-tive model for the HSCT combustor environment. The Phase I results will be an analyti-cal proof-of-concept, characterization of the anticipated benefits and generation of mixer designs suitable for verification testing in Phase II. This program targets the de-fined Subtopic need for environmentally and economically compatible improvements directed at combustors for supersonic transport propulsion systems.
