Characterization and wall compatibility testing of a 40K pound thrust class swirl-coaxial injector and calorimeter combustion chamberSubscale injector-combustor tests under the NASA Space Transportation Engine Thrust Chamber Technology program measured characteristic velocity (c-asterisk) efficiencies and wall heat fluxes for the pressure range 1710 psia to 2360 psia and for the overall O2/H2 mixture ratio range 5.5 to 6.4. Tests involving radially-uniform mixture ratio profiles produced c-asterisk efficiencies above 99 percent; nonuniform profiles associated with wall durability-enhancement schemes resulted in lower efficiencies. Though all three wall protection methods proved successful at reducing wall heat flux, scarfing of the outer-row, swirl-coaxial injection elements was the technique which resulted in the least debit in c-asterisk per unit reduction in heat flux.
Document ID
19910059416
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Petersen, E. L. (Pratt and Whitney Aircraft Group West Palm Beach, FL, United States)
Rozelle, R. (Pratt and Whitney Aircraft Group West Palm Beach, FL, United States)
Borgel, P. J. (Pratt and Whitney Group West Palm Beach, FL, United States)