Patent ID: 8016546

Claim:
A gas turbine engine comprising: a compressor section; a combustion section located downstream of the compressor section; a turbine section located downstream of the combustion section and having multiple vane assemblies; a first of the vane assemblies having a platform and a vane airfoil, the platform having a vane mounting surface and a cooling channel; and the cooling channel being defined by a cooling surface and a substantially planer, plate-shaped channel cover, the channel cover being wider at an upstream side than at a downstream side, the channel cover being spaced from the cooling surface, the cooling surface being positioned between a gas flow path of the vane and the channel cover, the channel having a cooling air inlet located in a high pressure region of the platform and in said channel cover upstream side and a cooling air outlet located in a low pressure region of the platform and in said channel cover downstream side such that, during operation, cooling air flows into the cooling air inlet, through the cooling channel and out of the cooling air outlet without flowing into the vane airfoil.