Patent ID: 7811058
Filing Date: 2010-10-12
Classification: F01D,F05D,Y10S

Abstract:
1. An annular array of aerofoils for a gas turbine engine, the array defining a cooling arrangement comprising: a junction gap between overlapping pressure and suction platforms of adjacent aerofoils; a damper being located radially inwardly of the junction gap; a damper surface; and a platform suction surface arranged to have a coolant flow passing between said platform suction surface and said damper surface in use, and a hot gas secondary flow passing, in use, from said pressure platform to said suction platform, wherein said junction gap is at an angle relative to a radial line to angularly present a coolant flow in use adjacent to an exit of the junction gap and substantially in the same direction as said hot gas secondary flow to form a continuous film onto the platform suction surface in use.