Abstract: A two-phase type heat transfer device (10) for heat sources operating at a wide temperature range. The heat transfer device (10) includes an evaporator (21) collecting heat from a heat source, a condenser (21) providing heat to a cold sink by a first working fluid passing through liquid and vapor transport lines (25, 27) that connect the evaporator (21) and the condenser (23). The evaporator (21) is arranged inside a saddle (31) configured for avoiding that the temperature of the first working fluid in the evaporator (21) is greater than its critical point. The invention also refers to aircraft ice protection systems using the heat transfer device (10).

Abstract: An ice protection device for an aircraft surface having a composite layer. The device comprises a layer of electrically conductive material configured to be located at an outer face of the composite layer and adapted to be heated by electromagnetic induction. The device also comprises a perimetric monophasic winding to heat an edge surrounding a delimited area of the electrically conductive layer, an inner monophasic or multiphasic winding to heat the inside of the delimited area of the perimetric monophasic winding, a control unit, to independently control the outer winding and the inner winding, the control unit being adapted to continuously operate the outer winding to avoid the formation of ice in the edge of the delimited area and also to operate the inner winding when the ice formed inside the delimited area is to be detached.

Abstract: A two-phase type heat transfer device (10) for heat sources operating at a wide temperature range. The heat transfer device (10) includes an evaporator (21) collecting heat from a heat source, a condenser (21) providing heat to a cold sink by a first working fluid passing through liquid and vapor transport lines (25, 27) that connect the evaporator (21) and the condenser (23). The evaporator (21) is arranged inside a saddle (31) configured for avoiding that the temperature of the first working fluid in the evaporator (21) is greater than its critical point. The invention also refers to aircraft ice protection systems using the heat transfer device (10).

Abstract: An ice protection device for an aircraft surface having a composite layer. The device comprises a layer of electrically conductive material configured to be located at an outer face of the composite layer and adapted to be heated by electromagnetic induction. The device also comprises a perimetric monophasic winding to heat an edge surrounding a delimited area of the electrically conductive layer, an inner monophasic or multiphasic winding to heat the inside of the delimited area of the perimetric monophasic winding, a control unit, to independently control the outer winding and the inner winding, the control unit being adapted to continuously operate the outer winding to avoid the formation of ice in the edge of the delimited area and also to operate the inner winding when the ice formed inside the delimited area is to be detached.

Abstract: Non-straight ducts for conducting fluids at temperatures higher than 280° C. and pressures higher than 4 bar made of a composite material and, particularly, hot air bleed ducts of an aircraft made of a carbon-fiber reinforced polymer aimed to reduce weight of the bleeding system by replacing most of the metallic material from which the bleeding ducts are currently made.