In this article, a re-cooled cycle (RCC) has been proposed for a regeneratively cooled scramjet to decrease the hydrogen fuel flow for cooling. In this method, the fuel heat sink (cooling capacity) is indirectly increased, and the fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle; this is done instead of carrying excess fuel for cooling or looking for a new coolant. Heat transfer effectivenesses of the cooling passage and pressure loss are introduced in the cycle, and cycle parameters are recomputed. An investigation of the effects of various irreversible losses on the RCC performance is carried out.
Irreversible cycle analysis of a re-cooled cycle for a scramjet
01.08.2010
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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