Electric de-icing device for turbojet engine nacelle element

Abstract

The present disclosure provides an electric de-icing/anti-icing device for a turbojet engine or turbo-prop nacelle element to be protected from icing. The device includes: a heating assembly including first and second heating stages positioned in the nacelle element; an electricity supply circuit delivering a primary voltage to the first heating stage of the heating assembly. In particular, the electricity supply circuit includes an electricity source, and a de-icing/anti-icing circuit which is connected to the heating assembly and supplied voltage by the electricity source. Furthermore, the de-icing/anti-icing device includes components to supply a complementary voltage to the second heating stage of the heating assembly.

What is claimed is: 
     
         1 . An electric de-icing/anti-icing device for a turbojet engine/turboprop nacelle element, comprising:
 a heating assembly comprising first and second heating stages disposed in the nacelle element to be protected from frost;   an electric energy power supply circuit delivering a principal voltage to the first heating stage, and comprising:   an electric power supply source,
 a de-icing/anti-icing circuit connected to the heating assembly and supplied with voltage by said electric power supply source; and 
   means for delivering a complementary voltage to the second heating stage of the heating assembly.   
     
     
         2 . The electric de-icing/anti-icing device according to  claim 1 , wherein the means for delivering the complementary voltage comprises:
 at least one temperature sensor positioned in the nacelle element to be protected from frost;   at least one contactor integrated to the de-icing/anti-icing circuit and also connected at an inlet to the electric power supply source and at an outlet to the second heating stage of the heating assembly; and   at least one control unit connected to the temperature sensor and to the contactor, adapted to alternatively control a passage of the contactor between an inhibited position in which the second heating stage is not supplied with a voltage and a closed position in which the second heating stage is supplied with a voltage.   
     
     
         3 . The electric de-icing/anti-icing device according to  claim 2 , wherein the control unit is integrated to the de-icing/anti-icing circuit. 
     
     
         4 . The de-icing/anti-icing device according to  claim 1 , wherein the electric power supply source is delivered by an airplane electric network. 
     
     
         5 . The de-icing/anti-icing device according to  claim 2 , further comprising:
 a power conversion stage supplied with alternating voltage by an airplane electric network and connected to the control unit, said power conversion stage being adapted to convert the alternating voltage delivered by the airplane electric network to variable direct voltage; and   a contactor, an inlet thereof connected to an outlet of a power conversion stage and the outlet connected to the second heating stage, said contactor being controlled by the control unit.   
     
     
         6 . The de-icing/anti-icing device according to  claim 1 , wherein the electric power supply source is constituted by an electric generator. 
     
     
         7 . The de-icing/anti-icing device according to  claim 6 , wherein the electric generator is further connected to the first heating stage of the heating assembly, and the de-icing/anti-icing circuit is constituted by a contactor of which an inlet is connected to said electric generator, and an outlet of the contactor connected to the second heating stage of the heating assembly, and said contactor being controlled by the control unit. 
     
     
         8 . The de-icing/anti-icing device according to  claim 1 , wherein the heating assembly comprises four heaters distributed on a periphery of the nacelle element to be protected from frost. 
     
     
         9 . A nacelle for a turbojet engine/turboprop comprising the de-icing/anti-icing device according to  claim 1 , wherein the heating assembly is integrated to an air inlet lip of the nacelle. 
     
     
         10 . A method of de-icing/anti-icing of a nacelle element for a turbojet engine or turboprop, said nacelle element comprising a de-icing/anti-icing device according to  claim 1 , said method comprising:
 identifying a temperature of a nacelle element;   delivering to the first heating stage of the heating assembly a variable principal voltage according to the identified temperature;   delivering to the second heating stage of the heating assembly a complementary voltage when a value of the identified temperature of the nacelle element to be protected from frost is lower than a predetermined temperature value.   
     
     
         11 . A method of de-icing/anti-icing of an aircraft element, said aircraft element comprising the de-icing/anti-icing device according to  claim 1 , said method comprising:
 identifying a temperature of an aircraft element;   delivering to the first heating stage of the heating assembly a variable principal voltage according to the identified temperature;   delivering to the second heating stage of the heating assembly a complementary voltage when a value of the temperature of the aircraft element to be protected from frost is lower than a predetermined temperature value.