Patent ID: 7438528

Claim:
An aerofoil component for a gas turbine engine having a cooling arrangement comprising: a supply passage within the component; a plurality of cooling passages comprising a first array of cooling passages and a second array of cooling passages, which open at respective discharge openings at a surface of the component, a first region of the component adjacent the supply passage that is provided with the first array of cooling passages which lie in a common plane, each cooling passage of the first array opening into the supply passage at its end away from its discharge opening, and a second region of the component extending from the first region to the discharge openings comprising the second array of cooling passages which lie in a common plane and the first array of cooling passages, more than one of each of the cooling passages of the second array intersect more than one of the cooling passages of the first array to provide fluid communication between the cooling passages of the first array, each of the cooling passages of the second array terminating short of the supply passage at its end away from its discharge opening at an intersection with the cooling passages of the first array.