SUCTION FUEL SYSTEMS FOR TURBINE POWERED AIRCRAFT

With respect to inlet pressure requirements, main fuel pumps for gas turbine engines have led a relatively sheltered life in the aviation market place. Traditionally, engine manufacturers have required positive fuel 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 aircraft application as an example, this paper describes the design, development and certification 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.