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oai:drum.lib.umd.edu:1903/20942016-03-29T06:48:55Zcom_1903_2206com_1903_1654com_1903_2col_1903_2737col_1903_3

Lewis, Mark J Clough, Joshua Alan Digital Repository at the University of Maryland University of Maryland (College Park, Md.) Aerospace Engineering 2005-02-02T06:44:07Z 2005-02-02T06:44:07Z 2004-12-01 http://hdl.handle.net/1903/2094 The fundamental performance of several TBCC engines is investigated from Mach 0-5. The primary objective of this research is the direct comparison of several TBCC engine concepts, ultimately determining the most suitable option for the first stage of a two-state-to-orbit launch vehicle. TBCC performance models are developed and optimized. A hybrid optimizer is developed, combining the global accuracy of probabilistic optimization with the local efficiency of gradient-based optimization. Trade studies are performed to determine the sensitivity of TBCC performance to various design variables and engine parameters. The optimization is quite effective, producing results with less than 1% error from optimizer repeatability. The turbine-bypass engine (TBE) provides superior specific impulse performance. The hydrocarbon-fueled gas-generator air turborocket and hydrogen-fueled expander-cycle air turborocket are also competitive because they may provide greater thrust-to-weight than the TBE, but require some engineering problems to be addressed before being fully developed. 3051768 bytes application/pdf en_US Modeling and Optimization of Turbine-Based Combined-Cycle Engine Performance Thesis Engineering, Aerospace TBCC combined-cycle engines turboramjet air turborocket airbreathing engine TSTO open.access