This study evaluates the influence of fuel temperature limits and engine lubricant temperature limits on installed interceptor performance at the airframe subsystem and engine component level. Engine cycles, representative of technology levels necessary to provide high Mach, steady-state cruise capability in the 1980 time period, were selected. Definition of these concepts permitted evaluation of engine performance as a function of fuel and lubricant properties and temperature limitations. Installed performance increments then were determined for advanced interceptors using takeoff gross weight in a fixed mission role as the primary figure of merit. This allowed a measure of the relative performance significance of airframe subsystem and engine component design changes. The relative allotment of available fuel heat sink between engine and airframe was also investigated to determine the primary factors affected by fuel interface temperature which may influence aircraft performance, and to provide meaningful design guidance for future systems application.
Fuels and Lubricants Influence on Turbine Engine Design and Performance
1974
223 pages
Report
Keine Angabe
Englisch
PT6 gas turbine, lubricants and fuels
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