{"id":{"repo_id":"maryland","oai_identifier":"oai:drum.lib.umd.edu:1903/2094"},"canonical_url":"https://search.dev.ndltd.org/etd/maryland/oai:drum.lib.umd.edu:1903/2094","repository":{"repo_id":"maryland","name":"University of Maryland","base_url":"https://api.drum.lib.umd.edu/server/oai/request"},"display":{"title":"Modeling and Optimization of Turbine-Based Combined-Cycle Engine Performance","abstract":"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.","abstract_html":"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.","abstract_has_math":false,"creators":["Clough, Joshua Alan"],"institution":null,"degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Aerospace Engineering","school":null,"contributors":[],"advisors":["Lewis, Mark J"],"committee_chairs":[],"committee_members":[],"year":2004,"date_issued":"2004-12-01","date_published":"2004-12-01","updated_at":"2026-07-24T03:02:17Z","subjects":[],"languages":["en_US"],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/1903/2094","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Lewis, Mark J"]},{"key":"dc:contributor.department","label":"Department","values":["Aerospace Engineering"]},{"key":"dc:creator","label":"Author","values":["Clough, Joshua Alan"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2005-02-02T06:44:07Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2005-02-02T06:44:07Z"]},{"key":"dc:date.issued","label":"Date","values":["2004-12-01"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language.iso","label":"Language (ISO)","values":["en_US"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["http://hdl.handle.net/1903/2094"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["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."]},{"key":"dc:format.mimetype","label":"Dc Format Mimetype","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Modeling and Optimization of Turbine-Based Combined-Cycle Engine Performance"]}]}],"canonical_facts":{"dc:contributor.advisor":["Lewis, Mark J"],"dc:contributor.department":["Aerospace Engineering"],"dc:creator":["Clough, Joshua Alan"],"dc:date.accessioned":["2005-02-02T06:44:07Z"],"dc:date.available":["2005-02-02T06:44:07Z"],"dc:date.issued":["2004-12-01"],"dc:description.abstract":["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."],"dc:format.mimetype":["application/pdf"],"dc:identifier.uri":["http://hdl.handle.net/1903/2094"],"dc:language.iso":["en_US"],"dc:title":["Modeling and Optimization of Turbine-Based Combined-Cycle Engine Performance"],"dc:type":["Thesis"]},"updated_at":"2026-07-24T03:02:17Z"}