V/STOL Plenum Chamber Combustion Research Study.
Final rept. 15 Feb 64-14 Feb 65 on Phase 1,
NAVAL AIR ENGINEERING CENTER PHILADELPHIA PA AERONAUTICAL ENGINE LAB
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A research program was initiated on combustion in the fan duct of a turbofan engine configured for VStol and supersonic flight at altitude. An analysis of the operating conditions for a typical application was made. Several methods of supporting combustion under these conditions and in the space available were considered. Experimental research was carried out on eighteen combustion chamber liners of the can type, sixteen of which were of experimental design for this program. Correlations were made among various performance parameters and between design factors and performance. A design which promises to meet requirements was developed. Author
- Combustion and Ignition
- Jet and Gas Turbine Engines