Adaptive thermal management system for aircraft fuel system
An adaptive thermal management system for a gas turbine engine includes a heat exchanger transferring heat into a coolant, a temperature sensor measuring a temperature of the coolant, and a sensor assembly that measures a parameter of the coolant during operation of the gas turbine engine. The parameter measured by the sensor assembly is indicative of a capacity of the coolant to accept heat from the hot flow. A control valve governs a flow of coolant into the heat exchanger. A controller adjusts the control valve to communicate coolant to the heat exchanger based on a determined capacity of the coolant to accept heat in view of the measured temperature of the coolant and that the measured parameter of the coolant is within a predefined range.
1. An adaptive thermal management system for a gas turbine engine comprising:
a heat exchanger transferring heat into a coolant;
a temperature sensor measuring a temperature of the coolant;
a sensor assembly measuring a parameter of the coolant during operation of the gas turbine engine, the parameter measured by the sensor assembly is indicative of a capacity of the coolant to accept heat;
a control valve governing a flow of coolant into the heat exchanger; and
a controller adjusting the control valve to communicate coolant to the heat exchanger based on a determined capacity of the coolant to accept heat in view of the measured temperature of the coolant and that the measured parameter of the coolant is within a predefined range wherein the coolant comprises fuel from a fuel system, the fuel system including a fuel tank holding a mass of fuel and at least one fuel pump communicating fuel to the heat exchanger.
2. The adaptive thermal management system as recited in claim 1 , wherein the sensor assembly comprises a fuel mass sensor that measures a fuel mass within the fuel tank.
3. The adaptive thermal management system as recited in claim 1 , wherein the sensor assembly comprises an oxygen sensor measuring an oxygen content within the fuel.
4. The adaptive thermal management system as recited in claim 1 , wherein the controller is configured to utilize a current engine operating condition in determining the capacity of the coolant to accept heat.
5. The adaptive thermal management system as recited in claim 1 , wherein the controller is configured to utilize a current ambient operating condition in determining the capacity of the coolant to accept heat.
6. The adaptive thermal management system as recited in claim 1 , wherein the controller is configured to stop flow of coolant to at least one heat generating system in response to the capacity of the coolant or accepting heat being outside the predefined range.
7. A gas turbine engine comprising:
a fan rotatable within a fan nacelle;
a core engine including a compressor communicating compressed air to a combustor where compressed air is mixed with fuel and ignited to generate a high-energy gas flow expanded through a turbine;
a fuel system including a fuel tank containing a mass of fuel and a fuel pump for generating a fuel flow;
a heat exchanger receiving a portion of fuel flow for transferring heat from at least one heat generating system into the fuel flow;
a temperature sensor measuring a temperature of the fuel;
a sensor assembly measuring a parameter of the fuel during operation of the gas turbine engine, the parameter measured by the sensor assembly is indicative of a capacity of the fuel to accept heat;
a control valve governing a flow of fuel into the heat exchanger; and
a controller adjusting the control valve to communicate fuel flow to the heat exchanger based on a determined capacity of the fuel to accept heat in view of the measured temperature of the fuel and that the measured parameter of the fuel is within a predefined range.
8. The gas turbine engine as recited in claim 7 , wherein the measured parameter comprises an oxygen content of the fuel flow and the mass of fuel within the fuel tank.
9. The gas turbine engine as recited in claim 8 , wherein the temperature sensor comprises a first temperature sensor measuring a temperature of the fuel mass within the fuel tank and a second temperature sensor measuring a temperature of fuel flow downstream of the fuel tank, wherein a difference between a temperature of the fuel mass and the fuel flow is indicative of the capacity of the fuel to accept heat.
10. The gas turbine engine as recited in claim 7 , wherein the controller is configured to utilize a current engine operating condition in determining the capacity of the fuel to accept heat.
11. The gas turbine engine as recited in claim 10 , wherein the controller is configured to stop flow of fuel to at least one heat generating system in response to the capacity of the fuel for accepting heat being outside the predefined range.
12. A method of actively managing thermal loads comprising:
measuring a current temperature of a fuel during operation of a gas turbine engine;
measuring a fuel mass contained within the fuel system in addition to the current temperature of the fuel during operation of the gas turbine engine;
determining that the measured fuel mass is within a predefined range in view of the measured temperature that is indicative of a capacity of the fuel to accept additional heat input; and
transferring heat into the fuel in response to the measured fuel mass being within the predefined range in view of the measured temperature.
13. The method as recited in claim 12 , wherein the fuel is supplied to a combustor of the gas turbine engine through a fuel system and a portion of a flow of fuel is routed through a heat exchanger for transferring heat from another system into the fuel.
14. The method as recited in claim 13 , further including measuring an oxygen content within the fuel and transferring heat into the fuel in response to the measured oxygen content within the fuel being within a predefined range.
15. The method as recited in claim 13 , including determining a time in a flight cycle and adjusting the predefined range in view of the determined time in the flight cycle.
16. The method as recited in claim 13 , including determining a heat load of a heat generating system and transferring a portion of the heat load to the fuel in response to a determination that the fuel has additional capacity for accepting heat without exceeding a predefined temperature.
17. The method as recited in claim 12 , including stopping a transfer of heat into the fuel in response to a determination that the fuel mass or the temperature of the fuel is outside of the predefined range indicating that the fuel does not have a sufficient capacity to accept additional heat.
18. The method as recited in claim 17 , including monitoring the temperature of the fuel and reinitiating the transfer of heat into the fuel in response to the temperature of the fuel being within the predefined range indicating the fuel has some capacity to accept additional heat.