US 12,110,827 B1
Fuel systems for aircraft engines
Jeffrey D. Rambo, Evendale, OH (US); Scott G. Edens, Evendale, OH (US); and Michael Joseph Murray, Evendale, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 3, 2023, as Appl. No. 18/311,660.
Int. Cl. F02C 7/236 (2006.01); F02C 7/32 (2006.01)
CPC F02C 7/236 (2013.01) [F02C 7/32 (2013.01); F05D 2220/323 (2013.01); F05D 2270/07 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbo engine for an aircraft, the turbo engine comprising:
a gas turbine engine having a combustion section; and
a fuel system to provide pressurized fuel to the combustion section, the fuel system including:
a fuel tank;
a boost pump and a main pump driven by an accessory gearbox that is powered by a shaft of the turbo engine, the boost pump and the main pump arranged in series;
first and second temperature sensors to measure a temperature difference fuel across the boost pump and the main pump;
an auxiliary pump; and
a controller configured to:
compare the temperature difference to a threshold; and
operate the fuel system in (1) a first mode in which the boost pump and the main pump produce pressurized fuel for the turbo engine and the auxiliary pump is deactivated when the temperature difference is below the threshold, and (2) a second mode in which the auxiliary pump is activated and produces the pressurized fuel for the turbo engine while bypassing the boost pump and the main pump when the temperature difference exceeds the threshold.