Abstract
Lower engine fuel consumption has become a dominant factor in turbofan engine design owing to rapidly increasing fuel costs. One engine component with a large impact on engine performance is the exhaust system. Previous exhaust system studies have demonstrated the significant exhaust system efficiency gains available through mixing of the core and bypass flows. Typically, an extensive, costly rig and engine program is required to develop and optimize these gains. The purpose of this paper is to present the results of the low-cost design system used for the NASA/Garrett quiet, clean, general aviation turbofan (QCGAT) mixer nozzle design and development. The scale model and full-scale engine test results confirm the predicted 3-5% reduction in cruise fuel consumption. This unique design system, which is based on integrating advanced three-dimensional viscous numerical methods with empirical optimization techniques, is summarized and detailed comparisons with test data are presented. The ability to accurately predict relative performance of mixer systems with substantially reduced development time and cost savings is demonstrated.
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