Aircraft heat management
A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 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, the gas turbine engine comprising:
an engine core comprising a combustor arranged to burn a fuel; a turbine, the turbine comprising a plurality of turbine blades; a compressor arranged to be used as a source of cooling air for the turbine blades; and an inducer arranged to accelerate and direct the cooling air onto the turbine blades and comprising a plurality of airflow passageways, and a modulating valve arranged to allow or block cooling air flow into a subset of the passageways; 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 fuel-oil heat exchangers arranged to transfer heat between the oil and the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger;
wherein the method comprises:
using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and
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.
2. The method of claim 1 , wherein the method comprises transferring 300-500 kJ/m 3 of heat to the fuel in the primary fuel-oil heat exchanger at cruise conditions.
3. The method of claim 1 , wherein the method comprises transferring 350-450 kJ/m 3 of heat to the fuel in the primary fuel-oil heat exchanger at cruise conditions.
4. The method of claim 1 , wherein the method comprises transferring 400 kJ/m 3 of heat to the fuel in the primary fuel-oil heat exchanger at cruise conditions.
5. The method of claim 1 , wherein the secondary fuel-oil heat exchanger is a servo fuel-oil heat exchanger.
6. The method of claim 1 , wherein between 10% and 30% of the fuel is delivered to the secondary fuel-oil heat exchanger.
7. The method of claim 1 , wherein between 10% and 20% of the fuel is delivered to the secondary fuel-oil heat exchanger.
8. The method of claim 1 , wherein, for fuel that passes through both fuel-oil heat exchangers, a ratio of heat transfer from the oil to the fuel for the primary and secondary fuel-oil heat exchangers is between 70:30 and 90:10.
9. The method of claim 1 , wherein, for fuel that passes through both fuel-oil heat exchangers, a ratio of heat transfer from the oil to the fuel for the primary and secondary fuel-oil heat exchangers is approximately 80:20.
10. 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.
11. The method of claim 1 , wherein:
the fuel management system further comprises:
a recirculation valve located downstream of the primary fuel-oil heat exchanger and between the primary fuel-oil heat exchanger and the combustor, 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 the inlet of the primary fuel-oil heat exchanger; and
wherein fuel flow through the fuel-oil heat exchangers is at least partially controlled by controlling the fuel amount to be returned to the inlet of the primary fuel-oil heat exchanger.
12. The method of claim 1 , wherein fuel that passes through the secondary fuel-oil heat exchanger is not sent to the combustor, such that all heat transferred from the oil to fuel which reaches the combustor is transferred in the primary fuel-oil heat exchanger.
13. A gas turbine engine for an aircraft, the gas turbine engine comprising:
an engine core comprising a combustor arranged to burn a fuel; a turbine, the turbine comprising a plurality of turbine blades; a compressor arranged to be used as a source of cooling air for the turbine blades; and an inducer arranged to accelerate and direct the cooling air onto the turbine blades and comprising a plurality of airflow passageways and a modulating valve arranged to allow or block cooling air flow into a subset of the passageways, wherein the modulating valve is configured to adjust the cooling air flow based on turbine inlet temperature; 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 fuel-oil heat exchangers arranged to transfer heat between the oil and the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger;
and wherein the fuel management system is arranged to transfer 200-600 kJ/m 3 of heat to the fuel in the primary fuel-oil heat exchanger at cruise conditions.
14. The gas turbine engine of claim 13 , wherein the fuel management system is arranged to transfer 300-500 kJ/m 3 of heat to the fuel in the primary fuel-oil heat exchanger at cruise conditions.
15. The gas turbine engine of claim 13 , wherein the fuel management system is arranged to transfer 350-450 kJ/m 3 of heat to the fuel in the primary fuel-oil heat exchanger at cruise conditions.
16. The gas turbine engine of claim 13 , wherein the secondary fuel-oil heat exchanger is a servo fuel-oil heat exchanger.
17. The gas turbine engine of claim 13 , wherein between 10% and 30% of the fuel is delivered to the secondary fuel-oil heat exchanger.
18. The gas turbine engine of claim 13 , wherein between 10% and 20% of the fuel is delivered to the secondary fuel-oil heat exchanger.
19. The gas turbine engine of claim 13 , wherein a ratio of heat transfer from the oil to the fuel for the primary and secondary fuel-oil heat exchangers is between 70:30 and 90:10.
20. The gas turbine engine of claim 13 , 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.