Patent ID: 7524163
Filing Date: 2009-04-28
Classification: F01D,F05B,F05D

Abstract:
1. A turbine nozzle guide vane for a gas turbine engine having a main hollow core and a casing wherein air flows in use from a forward end downstream to a rear end of said hollow core and wherein the nozzle guide vane includes inner and outer platforms with an aerofoil extending therebetween, at least one platform comprises a front sealing rail, a rear sealing rail for mechanically fixing the nozzle guide vane to the casing for sealing a working fluid against leakage and an abutment face with said rear sealing rail being located closer to said rear end of said hollow core than said front sealing rail, a seal strip slot is defined in the abutment face and is fed cooling air via at least one passage defined in the platform wherein the at least one passage has an outlet located within said seal strip slot, upstream of the rear sealing rail and downstream of the front sealing rail, to deliver cooling air into the strip seal slot upstream of the rear sealing rail wherein the passage extends from the main hollow core in the respective platform to the seal strip slot to supply cooling air from the main hollow core to the seal strip slot.