Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
<p> Design, build, and test a 5,000 lbf thrust regeneratively cooled combustion chamber at JSC for a low pressure liquid oxygen/methane engine. The engine demonstrates its effectiveness by continuous steady state operation without catastrophic damage to the combustion chamber.</p> <p> This project will advance in three phases:&nbsp; 1)&nbsp; The addition of a regeneratively cooled test section to an existing pressure fed LOX/Methane engine.&nbsp; This &quot;partial regen&quot; engine will be hot fire tested and thereby used to validate a multiphase regen cooling model. &nbsp; 2) The development of a tube forming technique to construct a low cost full-size regeneratively cooled combustion chamber. &nbsp; 3)&nbsp; Using the results of #1 and 2, create a full scale regeneratively cooled combustion chamber (open loop cooling) for an existing 5,000 lbf subcritical liquid oxygen/methane rocket engine with variable chamber heat load capability.&nbsp;&nbsp; This full scale engine will be hot fire tested to demonstrate performance.&nbsp;</p>