Nozzle guide vanes

Abstract

A turbine nozzle guide vane with passages leading from a hollow core to respective seal strip slots, to deliver cooling air to abutment faces on each end of the vane.

1 . A turbine nozzle guide vane for a gas turbine engine, the nozzle guide vane including a pair of platforms with an aerofoil extending therebetween, seal strip slots provided on each end of each platform characterised in that passages are provided extending within the nozzle guide vane from the respective platforms to the respective seal strip slots for delivering cooling air to the respective abutment faces of the guide vanes.  
   
   
       2 . A turbine nozzle guide vane according to  claim 1 , characterised in that the passages extend from a main hollow core in the respective platforms to the seal strip slots.  
   
   
       3 . A turbine nozzle guide vane according to  claim 2 , characterised in that the passages are inclined relative to the main hollow core.  
   
   
       4 . A turbine nozzle guide vane according to  claim 1 , characterised in that a plurality of passages extend to each seal strip slot.  
   
   
       5 . A turbine for a gas turbine engine, the turbine including a plurality of nozzle guide vanes arranged in one or more rings, characterised in that the nozzle guide vanes are according to  claim 1 .  
   
   
       6 . A method of forming turbine nozzle guide vanes for a gas turbine engine, the method including investment casting metal around a core member, which core member defines openings in the guide vane, subsequently removing the core member, characterised in that projections on the core member define passages extending into where seal strip slots are provided.  
   
   
       7 . A method according to  claim 6 , characterised in that the seal strip slots are machined into the nozzle guide vanes following removal of the core member therefrom, so as to expose ends of said passages in the slots.