Date of Award
Master of Science in Aeronautical Engineering
Department of Aeronautics and Astronautics
Richard D. Branam, PhD
An initial design of a split flow liquid hydrogen turbopump for the Dual Expander Aerospike Nozzle (DEAN) upper stage engine was completed. The engine nozzle is an annular aerospike. The engine cycle requires a combustion chamber pressure of 1,740 psia. The DEAN is designed to deliver 57,200 lbf of thrust and 472 seconds of Isp. The turbopump design was completed using a meanline software tool. The design consists of a single piece rotor, with a two-stage pump and radial inflow turbine. The turbopump flow rates are 15.1 and 7.55 lbm/s into the first and second stage, respectively. The first and second stage pumps use unshrouded impellers. An interstage transfer models the fluid split flow. The fluid for each stage exits through a volute. The first and second stage impeller hub-tip ratios are 0.3 and 0.35, respectively. The turbine is a full admission reaction type. At the design condition, the turbine delivers 3,607 horsepower at a total pressure ratio of 1.84.
DTIC Accession Number
Arguello, Michael A., "The Concept Design of a Split Flow Liquid Hydrogen Turbopump" (2008). Theses and Dissertations. 2672.