Heat transfer arrangement for fluid-washed surfaces

A gas turbine engine comprising an anti-icing arrangement for an aerofoil body having first and second ends and a fluid-washed surface extending there-between, said arrangement comprising:

• a heat transfer member extending from the first end at least part way along the body towards the second end;
• a heat source arranged in use to heat the heat transfer member in the vicinity of the first end of the body;
• and,
• a plurality of thermal control layers on said heat transfer member, each of said layers having a different thermal conductivity and being juxtaposed so as to create a thermal conductivity profile which varies along the length of the member.

A heat transfer arrangement for a fluid-washed body having first and second ends and a fluid-washed surface extending there-between, said arrangement comprising:

• a heat transfer member extending from the first end at least part way along the body towards the second end;
• a heat source arranged in use to heat the heat transfer member in the vicinity of the first end of the body;
• and,
• a thermal control layer on said heat transfer member, said layer having a varying thermal conductivity along its length so as to create a thermal conductivity profile which varies along the length of the member.