This paper discusses design and development of an advanced expander combustion chamber for a 50,000 pound (222.4 kN) thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Technology (IHPRPT) program. The Advanced Expander Combustor is designed to provide increased heat pick-up to the coolant and improved system thrust to weight, increased specific impulse, and increased reliability. These benefits will be accomplished and demonstrated through design, development, and test of this high heat flux, compact thrust chamber capable of supporting a chamber pressure of 1375 psia (97 kg/sq cm) in an expander cycle configuration.
Design and Development of an Advanced Expander Combustor
1998
13 pages
Report
Keine Angabe
Englisch
Design and development of an advanced expander combustor
AIAA | 1998
|Development and test of an advanced expander combustor
AIAA | 1999
|Development and Test of an Advanced Expander Combustor
NTIS | 1999
|Fabrication and test of an advanced expander combustor
AIAA | 2000
|Fabrication and Test of an Advanced Expander Combustor
NTIS | 2000
|