Gas turbine engine and method of operating gas turbine engine
A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor. The fuel management system comprises two fuel-oil heat exchangers through which oil and the fuel flow, the heat exchangers arranged to transfer heat to the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the two heat exchangers. The method comprises controlling the fuel management system so as to transfer between 200 and 600 kJ/m 3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.
1. A method of operating a gas turbine engine installed on an aircraft,
the gas turbine engine comprising:
a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor,
wherein the fuel management system comprises:
two fuel-oil heat exchangers through which oil and the fuel flow, the two fuel-oil heat exchangers arranged to transfer heat to the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger; and
a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the two fuel-oil heat exchangers;
wherein the method comprises:
operating the gas turbine engine at cruise conditions; and
controlling the fuel management system so as to transfer heat to the fuel from the oil in the primary fuel-oil heat exchanger in an amount between 200 and 600 kJ/m 3 of heat per unit volume of fuel reaching the combustor at cruise conditions.
2. The method of claim 1 , wherein the fuel management system is controlled so as to transfer heat to the fuel from the oil in the primary fuel-oil heat exchanger in an amount between 300 and 500 kJ/m 3 of heat per unit volume of fuel reaching the combustor at cruise conditions.
3. The method of claim 1 , wherein the fuel management system is controlled so as to transfer heat to the fuel from the oil in the primary fuel-oil heat exchanger in an amount between 350 and 450 kJ/m 3 of heat per unit volume of fuel reaching the combustor at cruise conditions.
4. The method of claim 1 , wherein:
the fuel management system further comprises:
a recirculation valve located downstream of the primary fuel-oil heat exchanger, the recirculation valve arranged to allow a controlled amount of fuel which has passed through the primary fuel-oil heat exchanger to be returned to an inlet of the primary fuel-oil heat exchanger; and
wherein the controlling the fuel management system comprises proportioning the controlled amount of the fuel returned to the inlet of the primary fuel-oil heat exchanger via the recirculation valve.
5. The method of claim 4 , wherein the gas turbine engine comprises a fuel metering valve downstream of the recirculation valve and arranged to control a fuel flow rate and to provide information on fuel flow, and wherein the controlling the fuel management system comprises controlling the fuel metering valve and the recirculation valve based on the information provided by the fuel metering valve.
6. The method of claim 1 , wherein:
the fuel management system further comprises:
a bypass pipe arranged to allow a proportion of the fuel to bypass the primary fuel-oil heat exchanger;
and wherein the controlling the fuel management system comprises controlling the proportion of the fuel which passes through the bypass pipe instead of through the primary fuel-oil heat exchanger.
7. The method of claim 1 , wherein:
the fuel management system further comprises an oil bypass pipe arranged to allow a proportion of the oil to bypass at least one of the primary fuel-oil heat exchanger and the secondary fuel-oil heat exchanger;
and wherein the controlling the fuel management system comprises controlling the proportion of the oil which passes through the oil bypass pipe instead of through the at least one heat exchanger.
8. The method of claim 1 , wherein between 10% and 30% of the fuel is delivered to the secondary fuel-oil heat exchanger.
9. The method of claim 1 , wherein between 10% and 20% of the fuel is delivered to the secondary fuel-oil heat exchanger.
10. The method of claim 1 , wherein a ratio of the heat transfer from the oil to the fuel for the primary and secondary fuel-oil heat exchangers is between 70:30 and 90:10.
11. The method of claim 1 , wherein a ratio of the heat transfer from the oil to the fuel for the primary and secondary fuel-oil heat exchangers is 80:20.
12. The method of claim 1 , wherein the fuel flows through the primary fuel-oil heat exchanger prior to flowing through the secondary fuel-oil heat exchanger whereas the oil flows through the secondary fuel-oil heat exchanger prior to flowing through the primary fuel-oil heat exchanger.