Patent ID: 9376918
Filing Date: 2016-06-28
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. An aerofoil for a gas turbine engine, the aerofoil comprising: a pressure wall, a suction wall and a web, wherein the web extends between the pressure wall and the suction wall, the suction wall comprises an inner leaf and an outer leaf that define a first cavity and a second cavity therebetween, the pressure wall defines a first outlet and a second outlet, at least one first passage extends from the first cavity through the web and to the first outlet, at least one second passage extends from the second cavity to the second outlet through the web wherein the pressure wall and the suction wall meet at a leading edge and at a trailing edge of the aerofoil, and the first cavity is closer to the leading edge than the second cavity.