Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection ot information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)2 ABSTRACTAdvances in materials and increases in turbopump efficiencies necessitate another look at the theoretical and practical limits for growth in chamber pressure and thrust in a liquid rocket expander cycle engine. The basic equations for turbopump power and heat flux rate out of the cooling jacket are examined to determine the theoretical limits for chamber pressure using an expander cycle. Turbopump efficiencies and operating speed limits for a LOX/H 2 expander engine are explored to determine practical limits as applied to the chamber pressure.
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