J-2 engine AS-502 /Apollo 6/ flight report S-2 and S-4B stages. Volume 2 - S-2 stage failure analysis
Postflight analysis of J-2 engine premature shutdown due to fuel system failure resulting in engine damage
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Postflight analysis of J-2 engine premature shutdown due to fuel system failure resulting in engine damage
Comparison performance data of compressor blading without slots or vortex generators
Analysis and design of compressor blading with slots and vortex generators
The aerodynamic design of a highly loaded multistage fan drive turbine is discussed. Turbine flowpath and airfoil sections are presented along with respective pressure and velocity distributions. Vibrational modes are identified in the expected turbine operating range.
An experimental program demonstrated that fuel-rich catalytic combustion can be accomplished soot free as long as the combustion temperature is less than the temperature at the rich limit of combustion. Although soot was not measured directly, three pieces of data strongly suggest that it was not present: (1) the product gases were completely transparent and produced no radiation characteristic of soot, (2) measured reaction temperatures followed closely those calculated for equilibrium with no soot present, and (3) over 99 percent of the carbon was accounted for in the measured reaction products. Data for two catalyst configurations were taken along with gas samples at two locations downstream of the catalyst bed.
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