CIRCUIT FOR DE-ICING AN AIR INLET LIP OF AN AIRCRAFT PROPULSION ASSEMBLY
Propulsion assembly, comprising a turbine engine surrounded by a nacelle comprising an annular air inlet lip, the propulsion assembly further comprising a circuit for lubricating elements of the turbine engine and a circuit for de-icing the air inlet lip, characterised in that said de-icing circuit comprises a heat exchanger comprising a primary circuit of oil supplied by said lubrication circuit and a secondary circuit of a heat transfer fluid for supplying at least one de-icing channel extending into said air inlet lip, said de-icing circuit further comprising a pump for circulating the heat transfer fluid into said at least one channel.
1 . Propulsion assembly, comprising a turbine engine surrounded by a nacelle comprising an annular air inlet lip, the propulsion assembly further comprising a circuit for lubricating elements of the turbine engine and a circuit for de-icing the air inlet lip, wherein said de-icing circuit comprises a heat exchanger comprising two superimposed heat exchange modules, including:
a first heat exchange module comprising a primary circuit of oil supplied by said lubrication circuit and a secondary circuit of a heat transfer fluid for supplying at least one de-icing channel extending into said air inlet lip, said de-icing circuit further comprising a pump for circulating the heat transfer fluid into said at least one de-icing channel,
and a second heat exchange module of the surface type and comprising an outer surface which is intended to be swept by a flow of cooling air.
2 . Propulsion assembly according to claim 1 , wherein the lip comprises two skins which are superimposed and define said at least one channel therebetween.
3 . Propulsion assembly according to claim 2 , wherein one of the skins defines an outer surface of the lip.
4 . Propulsion assembly according to claim 2 , wherein the skins define a single de-icing channel therebetween, which channel has a relatively small thickness and is designed to ensure the circulation of a film of heat transfer fluid.
5 . Propulsion assembly according to claim 2 , wherein the skins define a plurality of independent de-icing channels therebetween, which channels are each designed to ensure the circulation of heat transfer fluid.
6 . Propulsion assembly according to claim 5 , wherein one of the skins comprises hollow portions which are closed by the other of the skins to define said de-icing channels.
7 . Propulsion assembly according to claim 1 , wherein the lip is fixed to the rest of the nacelle by detachable fixing means.
8 . Propulsion assembly according to claim 1 , wherein said at least one de-icing channel has a general annular shape and is divided into sectors, each channel sector being connected to an inlet and to an outlet of heat transfer fluid, which are independent of the inlets and outlets of heat transfer fluid of the other channel sectors.
9 . Propulsion assembly according to claim 8 , wherein the fluid inputs of the channel sectors are connected to the pump by valves.
10 . Propulsion assembly according to claim 1 , wherein the heat exchanger is coupled to a surface exchanger, an outer surface of which is intended to be swept by a flow of cooling air.
11 . Propulsion assembly according to claim 1 , wherein said first module comprises a first fluid circulation chamber, which is part of the secondary fluid circuit, and wherein oil circulation manifolds extend, which are part of the primary oil circuit.
12 . Propulsion assembly according to claim 11 , wherein said second module comprises a second oil circulation chamber which is inserted between said first chamber and said outer surface.
13 . Propulsion assembly according to claim 1 , wherein said outer surface comprises projecting fins which are intended to increase the surface areas for heat exchange with said air flow.
14 . Propulsion assembly according to claim 11 , wherein said manifolds are independent of said second chamber.
15 . Propulsion assembly according to claim 11 , wherein a bypass system connects the manifolds and said second chamber.
16 . Propulsion assembly according to claim 15 , wherein said bypass system comprises a valve.
17 . Propulsion assembly according to claim 16 , wherein said valve is a thermostatic valve.
18 . Propulsion assembly according to claim 17 , wherein said thermostatic valve is designed to open the bypass when the temperature of the oil exceeds a specific threshold.