Device for protection against icing for aircraft engines and related de-icing method
View Patent ↗A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined threshold and a triggering system for launching a response to the detection of the crossing of the predetermined threshold, the response may be an alarm, an increase in the engine power delayed by the engine control system or the return of hot air upstream of the engine.
1. A device for protecting against ice accretion in aircraft engines at idling speed comprising at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring said amount and for comparing said amount to a predetermined threshold and a trigger system intended to initiate a response to a detection of the predetermined threshold being surpassed, wherein the trigger system is connected to an engine control system comprising means for governing engine idling speed, said response comprising an engine speed increase timed by the engine control system.
2. A device according to claim 1 , wherein the trigger system is connected to an alarm device and/or to a device for displaying an instruction to increase engine speed on the control panel of the aircraft, said response comprising triggering an alarm device and/or displaying the instruction.
3. A device according to claim 1 , wherein the trigger system and/or the engine control system are connected to means for measuring the temperature of the air intake of the engine and comprise means for managing the duration of the engine speed increase according to the temperature and the amount of ice measured.
4. A device according to claim 3 , wherein at least one of said measurement system and engine control system comprises storage means and computation means configured to accumulate the durations corresponding to the icing conditions and adapt the timing of the engine speed increase to said accumulation.
5. A device according to claim 1 , wherein said sensor comprises a surface probe built onto the surface of the engine subjected to icing and measuring an area of ice.
6. A device according to claim 1 , wherein said sensor comprises a vibrating finger probe subjected to the air flow entering the engine.
7. A device according to claim 1 , wherein the trigger system is connected to a system for expelling and returning hot air onto the upstream part of the engine.
8. A device according to claim 1 wherein said response comprises an engine speed increase up to 70% of a speed of an air blower of the aircraft engine.
9. A de-icing method for an aircraft engine at idling speed, comprising:
measuring an amount of ice on at least one wall of an engine element,
comparing the amount of ice measured to a predetermined threshold amount
triggering a response to the predetermined threshold being surpassed, and increasing the engine speed in response to the predetermined threshold being surpassed to perform a de-icing phase.
10. A method according to claim 9 , wherein increasing the engine speed comprises increasing the engine speed of up to 70% of a speed of an air blower of the aircraft engine.
11. A method according to claim 9 , comprising using the engine control system for delaying the engine speed increase according to the saved parameters that are representative of the duration of the icing conditions and increasing the engine speed according to said parameters.
12. A method according to claim 9 , comprising returning hot air to the upstream part of the engine in response to the predetermined threshold being surpassed.
13. A method according to claim 9 , comprising warning pilots of the aircraft with an alarm device that a de-icing phase is beginning or is going to begin.