The broadening of applications for smaller gas turbine engines has historically been impeded by the combined effects of relatively lower fuel efficiency and higher manufacturing cost, compared with competing propulsion/power systems. Broad systems analyses have determined that the applicability of small gas turbine engines can be greatly enhanced by combining coherent, complementary improvements in all the pertinent elements and components that affect engine fuel efficiency and cost. Achieving a best balance of attainments, avoiding significant compromises, is a vital imperative in this approach. API proposes a combustor development program based upon a number of significant, innovative design improvements that will yield a best balance of the large number of characteristics that have important effects on engine performance and cost, including integrity, reliability, maintenance cost and life. The proposed effort is specifically addressed to the problems of fuel efficiency and manufacturing cost of small gas turbine engines. The objective of the proposed effort is to achieve a high level of combustor performance, in terms of the conventional attributes by which combustors are judged, while substantially reducing manufacturing cost.General aviation light aircraft and helicopters, in gross weight classes less than 10,000 pounds, can benefit greatly by the increased use of lower cost, efficient gas turbine propulsion, including turbofan and turboshaft engines.combustor, gas turbine, turbofan, turboshaft, reduced-cost
