Fuel oxygen reduction unit for prescribed operating conditions
A fuel oxygen reduction unit for an engine is provided. The fuel oxygen reduction unit includes an inlet fuel line; a stripping gas source; a contactor selectively in fluid communication with the stripping gas source, the inlet fuel line, or both to form a fuel/gas mixture; and a separator that receives the fuel/gas mixture, the separator configured to separate the fuel/gas mixture into an outlet stripping gas flow and an outlet fuel flow; wherein a flow of stripping gas passes through the fuel oxygen reduction unit a single time.
1 . A method for operating a fuel delivery system for a gas turbine engine comprising:
receiving a stripping gas flow from a rechargeable bottle of stripping gas to a fuel oxygen reduction unit;
receiving an inlet fuel flow in the fuel oxygen reduction unit for reducing an amount of oxygen in the inlet fuel flow using the stripping gas flow through a stripping gas flowpath; and
passing the stripping gas flow through the fuel oxygen reduction unit a single time.
2 . The method of claim 1 , further comprising:
operating the gas turbine engine during an idle condition, wherein the gas turbine engine defines a turbine inlet temperature greater than 1000 degrees Fahrenheit while the gas turbine engine is operating during the idle condition.
3 . The method of claim 1 , wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit to reduce an oxygen content of a volume of fuel in a fuel nozzle of the gas turbine engine to less than 15 parts per million.
4 . The method of claim 1 , wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit substantially exclusively during a wind down condition.
5 . The method of claim 4 , further comprising:
providing a first flow of fuel to a fuel nozzle of the gas turbine engine during a second condition separate from the wind down condition, wherein a first oxygen content of the first flow of fuel to the fuel nozzle of the gas turbine engine during the second condition is greater than a second oxygen content of a volume of fuel in the fuel nozzle after ceasing providing the first flow of fuel to the fuel nozzle.
6 . The method of claim 5 , wherein the first oxygen content of the first flow of fuel to the fuel nozzle of the gas turbine engine during the second condition is at least 1.5 times greater than the second oxygen content of the volume of fuel in the fuel nozzle after ceasing providing the first flow of fuel to the fuel nozzle.
7 . The method of claim 5 , wherein the second condition is a flight condition.
8 . The method of claim 5 , wherein the second condition is a takeoff flight condition, a climb flight condition, or both.
9 . The method of claim 5 , wherein ceasing providing the first flow of fuel to the fuel nozzle of the gas turbine engine comprises maintaining the volume of fuel in the fuel nozzle during and after the wind down condition.
10 . The method of claim 4 , further comprising:
providing a second flow of fuel to a fuel nozzle of the gas turbine engine during a second condition separate from the wind down condition, wherein a first oxygen content of a volume of fuel in the fuel nozzle after ceasing providing the second flow of fuel to the fuel nozzle is a first value, wherein a second oxygen content of the second flow of fuel provided to the fuel nozzle during the second condition is a second value, and wherein the second value is equal to at least 1.5 times the first value.
11 . The method of claim 10 , wherein the second value is equal to at least 3 times the first value.
12 . The method of claim 10 , wherein the second condition is a flight condition.
13 . The method of claim 10 , wherein the second condition is a takeoff flight condition, a climb flight condition, or both.
14 . The method of claim 10 , further comprising:
providing a third flow of fuel to the fuel nozzle of the gas turbine engine during a third condition separate from the wind down condition, wherein a third oxygen content of the third flow of fuel provided to the fuel nozzle during the third condition is a third value, wherein the third value is less than the first value, wherein the second condition is a relatively high power flight condition, and wherein the third condition is a relatively low power flight condition.
15 . The method of claim 10 , wherein ceasing providing the second flow of fuel to the fuel nozzle of the gas turbine engine comprises maintaining the volume of fuel in the fuel nozzle during and after the wind down condition.
16 . The method of claim 3 , wherein the volume of fuel in the fuel nozzle is at least 10 milliliters of fuel.
17 . The method of claim 1 , further comprising:
operating the gas turbine engine during a cruise condition, wherein operating the gas turbine engine during the cruise condition comprises providing a fuel flow to a combustion section of the gas turbine engine at a cruise condition flowrate, wherein the fuel oxygen reduction unit defines a maximum fuel flowrate capacity, and wherein the maximum fuel flowrate capacity of the fuel oxygen reduction unit is less than the cruise condition flowrate.
18 . The method of claim 1 , wherein the gas turbine engine is incorporated into an aircraft, wherein the aircraft defines a maximum fuel capacity, wherein the fuel oxygen reduction unit defines a maximum volume of fuel throughput per flight mission, and wherein the maximum volume of fuel throughput is less than 10 percent of the maximum fuel capacity of the aircraft.
19 . The method of claim 1 , further comprising:
replenishing a supply of stripping gas to the rechargeable bottle of stripping gas using a stripping gas generator.
20 . The method of claim 1 , wherein the fuel oxygen reduction unit defines a maximum operating time of one hour or less per flight mission.