Aircraft gas turbine engine with heated fuel to assist combustion
An aircraft gas turbine includes a combustor that combusts compressed air and at least one fuel flow from at least one fuel source to generate combustion gases. A fuel supply system is arranged to provide at least one of a first flow of fuel to the combustor via a first fuel supply line and a second flow of a heated fuel to the combustor via a second fuel supply line. A fuel heat exchanger is arranged within the fuel supply system to generate the heated fuel that is heated above an autoignition temperature of the fuel, and a heat source communicates with the fuel heat exchanger for generating the heated fuel.
1. A method of operating an aircraft gas turbine engine, the aircraft gas turbine engine including (a) a combustor, (b) a fuel delivery system that provides fuel to the combustor, the fuel delivery system including a first fuel flow path and a second fuel flow path, (c) a fuel heat exchanger arranged in the second fuel flow path, and (d) a heat source in communication with the fuel heat exchanger, the method comprising:
operating the aircraft gas turbine engine in a standard operating mode by providing a compressed airflow and a fuel, via the first fuel flow path, to the combustor, and igniting the compressed air and the fuel in the combustor to generate combustion gases; and
operating the aircraft gas turbine engine in a relight mode by:
diverting at least a portion of the fuel from the first fuel flow path to the second fuel flow path such that the fuel flows through the fuel heat exchanger;
providing heat via the heat source to the fuel heat exchanger;
heating the fuel flowing through the fuel heat exchanger to a temperature above an autoignition temperature of the fuel to generate a heated fuel;
providing the heated fuel to the combustor; and
igniting the heated fuel in the combustor to relight the combustor.
2. The method according to claim 1 , the method further comprising, after the igniting the heated fuel in the combustor to relight the combustor discontinuing diverting the at least the portion of the fuel from the first fuel flow path to the second fuel flow path, and returning to operating the gas turbine engine in the standard operating mode.
3. The method according to claim 1 , wherein the aircraft gas turbine engine further includes a fuel oxygen reduction unit that generates a reduced oxygen fuel, and the reduced oxygen fuel is provided to the fuel delivery system.
4. The method according to claim 1 , wherein the combustor includes a first set of fuel nozzles in fluid communication with the first fuel flow path, and a second set of fuel nozzles in fluid communication with the second fuel flow path, and the heated fuel is provided to the combustor via the second set of fuel nozzles.
5. The method according to claim 1 , wherein the heat source includes a steam generating system arranged downstream of the combustor and in fluid communication with the fuel heat exchanger, and, in the providing heat via the heat source to the fuel heat exchanger, steam is provided via the steam generating system to the fuel heat exchanger.
6. The method according to claim 5 , wherein the fuel heat exchanger includes a fuel-steam mixer, and the providing heat via the heat source to the fuel heat exchanger includes mixing the steam and the fuel to generate the heated fuel.
7. The method according to claim 1 , wherein the diverting comprises a controller controlling a valve to adjust a percentage of the fuel flowing in the first fuel flow path and a percentage of the fuel flowing in the second fuel flow path.
8. The method according to claim 7 , wherein the providing heat is controlled by the controller to control an amount of the heating to be provided to the fuel heat exchanger so as to heat the fuel to above the autoignition temperature of the fuel.