Aircraft liquid heat exchanger anti-icing system

An aircraft anti-icing system comprising:

• a wing having a leading edge defining first exterior and interior surfaces;
• an engine coupled to the wing, the engine having an engine inlet defining second exterior and interior surfaces;
• a first liquid-to-air heat exchanger including a plurality of heated liquid-conveying tubes secured directly to the first interior surface, wherein heat is transferred from the tubes into the first interior surface;
• a second liquid-to-air heat exchanger including a plurality of heated liquid-conveying tubes secured directly to the second interior surface, wherein heat is transferred from the tubes into the second interior surface;
• and
• an air-to-liquid heat exchanger configured to selectively increase operational temperatures of anti-icing liquid conveyed to the first and second liquid-to-air heat exchangers using heat from engine bleed air transferred from the engine to the air-to-liquid heat exchanger;
• wherein the air-to-liquid heat exchanger is located at a fuselage of an associated aircraft, spaced away from wings and engines supported on the aircraft.

A method of making an aircraft anti-icing system, the method comprising the steps of:

• forming a liquid-to-air heat exchanger including a wing having a leading edge defining exterior and interior surfaces;
• securing a plurality of heated liquid-conveying tubes directly to the interior surface of the leading edge;
• forming an air-to-liquid heat exchanger located at a fuselage of an associated aircraft, spaced away from wings and engines supported on the aircraft;
• and
• forming a hot air bleed between at least one of the engines and the air-to-liquid heat exchanger to direct engine core bleed air to the air-to-liquid heat exchanger;
• wherein the air-to-liquid heat exchanger is configured to transfer heat to the liquid-to-air heat exchanger.