Sst parametric engine library: design

Technical Report · Thu Apr 30 04:00:00 EDT 1970

OSTI ID:7293798

Hill, D E; Scharf, W H

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.

• Research Organization: Boeing Co., Seattle, WA (USA). Commercial Airplane Group
• OSTI ID: 7293798
• Report Number(s): AD-906465; D-6A11786-1
• Country of Publication: United States
• Language: English

Related Subjects

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
320201 -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
33 ADVANCED PROPULSION SYSTEMS
330000* -- Advanced Propulsion Systems
AFTERBURNERS
AIRCRAFT
DESIGN
ENERGY CONSUMPTION
ENGINES
EQUIPMENT
FUEL CONSUMPTION
MATHEMATICAL MODELS
NOISE
PERFORMANCE
POLLUTION CONTROL EQUIPMENT
TURBOJET ENGINES
WEIGHT