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- W99796099 abstract "A description is given of a family of parametric engines of consistent technology developed to support production supersonic transport studies evaluating the effect of the engine cycle on noise and airplane performance. Engine design assumptions, performance, weights, and dimensions are presented. The parametric engines, both turbojets and turbofans, were designed at the Mach 2.7 supersonic cruise flight condition with a turbine inlet temperature of 2760 degrees R. The component performance levels are representative of the 1977 technology level and consistent with the predicted General Electric and Pratt and Whitney technology for that time period. The turbojets have been designed with compressor pressure ratios of 4, 5, 6, and 8 at supersonic cruise, in both afterburning and non-afterburning configurations. The turbofans are duct burning-forward fan engines with design supersonic cruise overall compressor pressure ratios of 4, 5, 6, and 8, and bypass ratios of 0.5, 1.0, 1.5, 2.0, 2.5 and 3.0 Fan pressure ratio for each turbofan engine was chosen for minimum cruise SFC, with variations at several lower fan pressure ratios to enable noise trades to be done. In all, 74 duct heating turbofans, 4 augmented turbojets, and 4 dry turbojets were designed." @default.
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- W99796099 date "1970-04-30" @default.
- W99796099 modified "2023-09-27" @default.
- W99796099 title "Sst parametric engine library: design" @default.
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