Advanced Materials and Cooling Schemes for Rocket Engine Combustion Chambers
Small Business Information
SIERRA ENGINEERING, INC.
603 E. Robinson Street,Suite 7, Carson City, NV, 89701
Jeffery Muss, PhD
AbstractWe will produce and test a flight-type transpiration cooled combustion chamber for high performance, reusable, liquid rocket engines utilizing a novel uniform pore material. The Sierra Engineering design produces a durable, low cost, flight-weighttranspiration cooled liner with integral fluid distribution and structural support hardware. The design will be based upon the rigorous analysis procedure and associated methodology developed under the Phase I project. The Phase I effort also fabricateda transporation cooled combustion chamber barrel segment and applied the design methodology and fabrication technique to a chamber concept for an NK-33 class hydrocarbon booster engine. The Phase II SBIR program shall: l)generate the data necessary toevaluate and improve the design methodology for a wide range of transpiration coolants, 2) demonstrate scale-up of the fabrication techniques from a heavy-weight research scale to a relevant flight-type booster class engine, and 3) produce a commerciallyviable 40 Klbf-class combustion chamber. Transpiration cooled combustion chamber technology has been demonstrated by others at a concept level, but flight weight hardware has never been developed.
* information listed above is at the time of submission.