Heat exhaust system for on-aircraft electric generator
A heat exhaust system for an on-aircraft electric generator, includes: a fuel pump which is driven by electric power generated by an electric generator installed in an aircraft, and which measures and supplies fuel to an engine of the aircraft; a first heat exchanger which releases heat generated by the electric generator into the fuel supplied to the engine; a fuel flow rate determiner which determines a flow rate of the fuel supplied to the engine by the fuel pump; an electric generator output determiner which determines an output from the electric generator; and a heat release controller which controls heat release at the first heat exchanger by using at least one of the flow rate of the fuel determined by the fuel flow rate determiner and the output determined by the electric generator output determiner as a control parameter.
1. A heat exhaust system for an on-aircraft electric generator, comprising:
a fuel pump driven by electric power generated by an electric generator installed in an aircraft, the fuel pump configured to measure and supply fuel to an engine of the aircraft;
a first heat exchanger configured to release heat generated by the electric generator into the fuel supplied to the engine;
a fuel flow rate determiner configured to determine a flow rate of the fuel supplied to the engine by the fuel pump;
an electric generator output determiner configured to determine an output from the electric generator; and
a heat release controller configured to control heat release at the first heat exchanger by using at least one of the flow rate of the fuel determined by the fuel flow rate determiner and the output determined by the electric generator output determiner as a control parameter.
2. The heat exhaust system for an on-aircraft electric generator according to claim 1 , wherein a single control device constitutes the fuel flow rate determiner, the electric generator output determiner, and the heat release controller.
3. The heat exhaust system for an on-aircraft electric generator according to claim 1 , wherein the heat release controller is configured to control the output from the electric generator by using the output determined by the electric generator output determiner as the control parameter.
4. The heat exhaust system for an on-aircraft electric generator according to claim 1 , further comprising:
a second heat exchanger configured to release the heat generated by the electric generator into air which is taken by a fan into a case of the engine, wherein
the heat release controller is configured to control heat release at the second heat exchanger.
5. The heat exhaust system for an on-aircraft electric generator according to claim 4 , further comprising:
a valve configured to adjust an amount of introduction of the heat generated by the electric generator into the first heat exchanger or the second heat exchanger, wherein
the heat release controller is configured to adjust an opening degree of the valve.
6. The heat exhaust system for an on-aircraft electric generator according to claim 2 , wherein the heat release controller is configured to control the output from the electric generator by using the output determined by the electric generator output determiner as the control parameter.
7. The heat exhaust system for an on-aircraft electric generator according to claim 2 , further comprising:
a second heat exchanger configured to release the heat generated by the electric generator into air which is taken by a fan into a case of the engine, wherein
the heat release controller is configured to control heat release at the second heat exchanger.
8. The heat exhaust system for an on-aircraft electric generator according to claim 7 , further comprising:
a valve configured to adjust an amount of introduction of the heat generated by the electric generator into the first heat exchanger or the second heat exchanger, wherein
the heat release controller is configured to adjust an opening degree of the valve.