US 12,031,492 B2
Electric fuel control closed loop aircraft fuel system
James Harder, Charlotte, NC (US); and Andrew W. Solomon, Windsor, CT (US)
Assigned to HAMILTON SUNDSTRAND CORPORATION, Charlotte, NC (US)
Filed by Hamilton Sundstrand Corporation, Charlotte, NC (US)
Filed on Oct. 12, 2021, as Appl. No. 17/498,855.
Prior Publication US 2023/0115336 A1, Apr. 13, 2023
Int. Cl. F02C 7/236 (2006.01); F02C 9/28 (2006.01); F02C 9/30 (2006.01); F04D 13/06 (2006.01)
CPC F02C 9/30 (2013.01) [F02C 7/236 (2013.01); F02C 9/28 (2013.01); F04D 13/06 (2013.01); F05D 2220/323 (2013.01); F05D 2270/301 (2013.01); F05D 2270/303 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A fuel control system for an aircraft comprising:
a first electric motor controlled fuel pump having an outlet operatively connected output pressurized fuel to a fuel line, and an inlet configured to receive fuel supplied from an aircraft fuel tank;
a second electric motor controlled fuel pump having an outlet operatively connected output pressurized fuel to the fuel line, and an inlet configured to receive fuel supplied from the aircraft fuel tank, wherein the first and second electric motor controlled fuel pumps connect in parallel with one another to the fuel line;
a plurality of fuel nozzles connected to the fuel line to issue pressurized fuel from the fuel line into a combustor, wherein at least one fuel nozzle in the plurality of fuel nozzles includes a respective sensor system; and
a fuel controller operatively connected to receive input from the respective sensor system of the at least one fuel nozzle, and operatively connected to control the first and second electric motor controlled pumps based on input from the respective sensor system of the at least one fuel nozzle, wherein the fuel controller is operatively connected to receive input from an engine controller, wherein the fuel controller is configured to control the first and second electric motor controlled pumps based on input from the respective sensor system of the at least one fuel nozzle and from the engine controller,
wherein each of the fuel nozzles in the plurality of fuel nozzles includes an inlet portion upstream, an outlet portion downstream with respect to the fuel flow and internal valving operatively connected to the fuel controller so the fuel controller can control fuel flow through the plurality of fuel nozzles by throttling the plurality of fuel nozzles and by controlling the first and second electric motor controlled pumps,
wherein the sensor system of the at least one fuel nozzle includes a pressure sensor on the outlet portion of the respective nozzle, the outlet portion is adjacent the combustor and configured to produce an input signal indicative of nozzle outlet pressure.