Icing protection system for an aircraft and method for operating an icing protection system
An icing protection system comprises a fuel cell, an evaporative cooling system, a thermal deicing device, a control unit and a device for measuring the pressure in the evaporative cooling system. The evaporative cooling system is in thermal contact with the fuel cell and with the thermal deicing device in order to conduct heat from the fuel cell to the thermal deicing device. The control unit controls the electrical power demanded from the evaporatively cooled fuel cell in dependence on a deviation of the pressure measured by the pressure measuring device from a predetermined NOMINAL pressure. In this way, an energetically very efficient and very well controllable icing protection system is made available that can be operated without bleed air supplied by engines or electrical energy provided by engine generators.
1. An icing protection system, comprising:
a fuel cell;
an evaporative cooling system,
a thermal deicing device with a condenser and steam conduits for supplying steam into the condenser,
a control unit, and
a device adapted to measure a pressure in the steam conduits and positioned in a wing nose,
wherein the evaporative cooling system is in thermal contact with the fuel cell to conduct heat from the fuel cell to the evaporative cooling system for the evaporation of a cooling medium and to route the evaporated cooling medium to the condenser via the steam conduits,
wherein the condenser is configured to condense the cooling medium evaporated during the operation of the fuel cell to cool the fuel cell while simultaneously emitting heat in the region to be deiced, and
wherein the control unit is configured to control the electrical power demanded from the evaporatively cooled fuel cell in dependence on a deviation of the pressure in the steam conduits measured with the pressure measuring device from a predetermined nominal pressure in such a way that the thermal cooling capacity of the evaporative cooling system of the evaporatively cooled fuel cell corresponds to the condensation capacity of the thermal deicing device.
2. The icing protection system of claim 1 , wherein the condenser is formed by at least a section of a wing nose.
3. The icing protection system of claim 1 , further comprising an electric icing protection system that is configured to receive electricity generated by the fuel cell system.
4. The icing protection system of claim 3 , wherein the electrical output of the electric icing protection system correlates with the thermal output of the thermal deicing device.
5. The icing protection system of claim 1 , wherein the cooling medium comprises water.
6. The icing protection system of claim 5 , further comprising a closable air inlet connected to the steam conduits to selectively flush the steam conduits and remove steam.
7. The icing protection system of claim 6 , wherein the air inlet is connected to a bleed air conduit of an engine.
8. A method of operating an icing protection system with a fuel cell, an evaporative cooling system and a thermal deicing device with a condenser, wherein the evaporative cooling system is in thermal contact with the fuel cell to conduct heat from the fuel cell to the evaporative cooling system for the evaporation of a cooling medium and to route the evaporated cooling medium to the condenser via the steam conduits, and wherein the condenser is configured to condense the cooling medium evaporated during the operation of the fuel cell to cool the fuel cell while simultaneously emitting heat in the region to be deiced, the method comprising:
measuring, by a pressure measuring device in a wing nose, a pressure in steam conduits, the steam conduits being used for supplying steam to regions to be deiced; and
controlling, by a control unit, an electrical power demanded from the fuel cell, wherein said controlling comprises adjusting the electrical power demanded from the evaporatively cooled fuel cell in dependence on a deviation of the pressure measured in the steam conduits with the pressure measuring device from a predetermined nominal pressure, and
wherein the electrical power demanded from the fuel cell is controlled in such a way that the thermal cooling capacity of the evaporative cooling system of the evaporatively cooled fuel cell corresponds to the condensation capacity of the thermal deicing device.
9. The method of claim 8 , wherein the steam mass flow supplied to the evaporative cooling system of the evaporatively cooled fuel cell due to evaporation and the steam mass flow lost at the thermal deicing device due to condensation are in equilibrium.
10. The method of claim 8 , wherein the steam mass flow supplied to the evaporative cooling system of the evaporatively cooled fuel cell is controlled in dependence on the steam mass flow lost at the thermal deicing device by a change in the pressure in the steam conduits.
11. The method of claim 8 , wherein the electric current generated by the evaporatively cooled fuel cell system is fed to an electric icing protection system.
12. The method of claim 8 , furthermore comprising flushing the steam conduits to remove steam.
13. An aircraft with an icing protection system in a wing nose, the icing protection system comprising:
a fuel cell;
an evaporative cooling system,
a thermal deicing device with a condenser and steam conduits for supplying steam into the condenser,
a control unit, and
a device arranged in the wing nose and adapted to measure the pressure in the steam conduits,
wherein the evaporative cooling system is in thermal contact with the fuel cell in order to conduct heat from the fuel cell to the evaporative cooling system for the evaporation of a cooling medium and to route the evaporated cooling medium to the condenser via the steam conduits,
wherein the condenser is configured to condense the cooling medium evaporated during the operation of the fuel cell in order to cool the fuel cell while simultaneously emitting heat in the region to be deiced, and
wherein the control unit is configured to control the electrical power demanded from the evaporatively cooled fuel cell in dependence on a deviation of the pressure in the steam conduits measured with the pressure measuring device from a predetermined nominal pressure in such a way that the thermal cooling capacity of the evaporative cooling system of the evaporatively cooled fuel cell corresponds to the condensation capacity of the thermal deicing device.