{"id":{"repo_id":"nps","oai_identifier":"oai:calhoun.nps.edu:10945/5767"},"canonical_url":"https://search.dev.ndltd.org/etd/nps/oai:calhoun.nps.edu:10945/5767","repository":{"repo_id":"nps","name":"Naval Postgraduate School","base_url":"https://calhoun.nps.edu/server/oai/request"},"display":{"title":"Transient heat transfer properties in a pulse detonation combustor","abstract":"The heat transfer along the axis of a pulse detonation combustor has been characterized for various frequencies and fill fractions at 2.5 atmospheres of pressure for chamber refresh conditions. In a pulse detonation combustor, a supersonic detonation wave is the method for transforming chemical energy into mechanical energy and the wave propagates much faster than the subsonic flames in devices such as rockets and ramjets. The flow field inside a pulse detonation combustor is highly turbulent, unsteady, and varies largely during each combustion cycle. By determining the heat transfer properties at multiple axial locations and the associated combustor wall temperatures, proper combustor material selection can ensure the material properties will not deteriorate and therefore allow for practical operational lifetimes. Experimental testing measured the axial heat transfer characteristics in a pulse detonation combustor at various operating conditions and multiple cooling jacket locations. Computer simulations were used to model the heat transfer inside the pulse detonation combustor and correlate those predications with empirical data. The acquired data from the comparison of the computer simulations and the experimental results was correlated and demonstrated good agreement. The determined values should allow designers the ability to consider regenerative fueling strategies for future systems.","abstract_html":"The heat transfer along the axis of a pulse detonation combustor has been characterized for various frequencies and fill fractions at 2.5 atmospheres of pressure for chamber refresh conditions. In a pulse detonation combustor, a supersonic detonation wave is the method for transforming chemical energy into mechanical energy and the wave propagates much faster than the subsonic flames in devices such as rockets and ramjets. The flow field inside a pulse detonation combustor is highly turbulent, unsteady, and varies largely during each combustion cycle. By determining the heat transfer properties at multiple axial locations and the associated combustor wall temperatures, proper combustor material selection can ensure the material properties will not deteriorate and therefore allow for practical operational lifetimes. Experimental testing measured the axial heat transfer characteristics in a pulse detonation combustor at various operating conditions and multiple cooling jacket locations. Computer simulations were used to model the heat transfer inside the pulse detonation combustor and correlate those predications with empirical data. The acquired data from the comparison of the computer simulations and the experimental results was correlated and demonstrated good agreement. The determined values should allow designers the ability to consider regenerative fueling strategies for future systems.","abstract_has_math":false,"creators":["Fontenot, Dion G."],"institution":"Monterey, CA; Naval Postgraduate School","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Mechanical and Aerospace Engineering (MAE)","school":null,"contributors":[],"advisors":["Brophy, Christopher M."],"committee_chairs":[],"committee_members":[],"year":2011,"date_issued":"2011-03","date_published":"2011-03","updated_at":"2026-07-27T20:26:05Z","subjects":[],"languages":[],"rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/10945/5767","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Brophy, Christopher M."]},{"key":"dc:contributor.department","label":"Department","values":["Mechanical and Aerospace Engineering (MAE)"]},{"key":"dc:creator","label":"Author","values":["Fontenot, Dion G."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2012-03-14T17:46:40Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2012-03-14T17:46:40Z"]},{"key":"dc:date.issued","label":"Date","values":["2011-03"]},{"key":"dc:publisher","label":"Institution","values":["Monterey, CA; Naval Postgraduate School"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:rights","label":"Dc Rights","values":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["https://hdl.handle.net/10945/5767"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["The heat transfer along the axis of a pulse detonation combustor has been characterized for various frequencies and fill fractions at 2.5 atmospheres of pressure for chamber refresh conditions. In a pulse detonation combustor, a supersonic detonation wave is the method for transforming chemical energy into mechanical energy and the wave propagates much faster than the subsonic flames in devices such as rockets and ramjets. The flow field inside a pulse detonation combustor is highly turbulent, unsteady, and varies largely during each combustion cycle. By determining the heat transfer properties at multiple axial locations and the associated combustor wall temperatures, proper combustor material selection can ensure the material properties will not deteriorate and therefore allow for practical operational lifetimes. Experimental testing measured the axial heat transfer characteristics in a pulse detonation combustor at various operating conditions and multiple cooling jacket locations. Computer simulations were used to model the heat transfer inside the pulse detonation combustor and correlate those predications with empirical data. The acquired data from the comparison of the computer simulations and the experimental results was correlated and demonstrated good agreement. The determined values should allow designers the ability to consider regenerative fueling strategies for future systems."]},{"key":"dc:title","label":"Title","values":["Transient heat transfer properties in a pulse detonation combustor"]}]}],"canonical_facts":{"dc:contributor.advisor":["Brophy, Christopher M."],"dc:contributor.department":["Mechanical and Aerospace Engineering (MAE)"],"dc:creator":["Fontenot, Dion G."],"dc:date.accessioned":["2012-03-14T17:46:40Z"],"dc:date.available":["2012-03-14T17:46:40Z"],"dc:date.issued":["2011-03"],"dc:description.abstract":["The heat transfer along the axis of a pulse detonation combustor has been characterized for various frequencies and fill fractions at 2.5 atmospheres of pressure for chamber refresh conditions. In a pulse detonation combustor, a supersonic detonation wave is the method for transforming chemical energy into mechanical energy and the wave propagates much faster than the subsonic flames in devices such as rockets and ramjets. The flow field inside a pulse detonation combustor is highly turbulent, unsteady, and varies largely during each combustion cycle. By determining the heat transfer properties at multiple axial locations and the associated combustor wall temperatures, proper combustor material selection can ensure the material properties will not deteriorate and therefore allow for practical operational lifetimes. Experimental testing measured the axial heat transfer characteristics in a pulse detonation combustor at various operating conditions and multiple cooling jacket locations. Computer simulations were used to model the heat transfer inside the pulse detonation combustor and correlate those predications with empirical data. The acquired data from the comparison of the computer simulations and the experimental results was correlated and demonstrated good agreement. The determined values should allow designers the ability to consider regenerative fueling strategies for future systems."],"dc:identifier.uri":["https://hdl.handle.net/10945/5767"],"dc:publisher":["Monterey, CA; Naval Postgraduate School"],"dc:rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"dc:title":["Transient heat transfer properties in a pulse detonation combustor"],"dc:type":["Thesis"]},"updated_at":"2026-07-27T20:26:05Z"}