A Variable Thrust Detonation Wave Engine DWE for Mach 0 to 3

An innovative actively cooled structure concept is proposed which integrates proven cooling techniques and state-of-the-art fabrication methods to extend the maximum combustor wall temperature, thereby reducing cooling requirements and aircraft weight while improving engine performance. Specifically, CONvective and TRANspiration cooling (CONTRAN) are uniquely combined, relying on hydrogen coolant to permeat a carbon-carbon structure providing oxidation and thermal protection. State-of-the art fabrication techniques will be used during Ph I to develop the desired carbon-carbon permeability specimen based on thermal and boundary layer analytical estimates and experimental testing refinements. Preliminary characteristics will be defined based on results from undensified and densified carbon-carbon permeability tests, thermal and structural analysis, and shock impingement and coolant compatibility reviews. In Ph II, final concept design verification models will be fabricated and tested in realistic flowing gas environment representative of the NASP engine combustor. Based on the concept verification tests, a prototype 20 by 20 inch test panel of a CONTRAN cooled NASP engine combustor wall will be designed and analyzed. Pending funding, Ph II could include the fabrication and testing of the 20 by 20 inch panel.