With respect to polyphase flow, main fuel pumps for gas turbine engines have led a relatively sheltered life in the general aviation market place. Traditionally, engine manufacturers have required positive fuel inlet pressures to eliminate the presence of free fuel vapor and air bubbles which tend to decrease volumetric efficiency and create cavitation conditions. Using an actual application as an example, this paper describes the design, development and performance evaluation of a self-contained, engine-driven suction fuel supply system that will operate continuously with a two-phase fuel flow while utilizing current state-of-the-art technology. This concept removes unreliable tank-mounted, electrical fuel boost pumps and eliminates airframe pressurized fuel handling equipment that will improve system reliability, reduce weight and cost penalties, simplify maintenance tasks, and reduce aircraft vulnerability to fire hazards. (Peters)
Suction fuel supply systems for turbine powered general aviation aircraft
Saug-Treibstoffversorgungssysteme fuer Flugzeugturbinen
1978
20 Seiten, 12 Bilder, 1 Tabelle, 3 Quellen
Aufsatz (Konferenz)
Englisch
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