Patent ID: 6270317
Filing Date: 2001-08-07
Classification: F01D,F05D,Y02T,Y10S

Abstract:
A turbine nozzle comprising:a plurality of vanes integrally joined at opposite ends to inner and outer bands;each of said vanes including opposite pressure and suction sidewalls extending in span longitudinally between said bands and chordally between leading and trailing edges;said sidewalls being spaced apart between said leading and trailing edges, and further including a first rib spaced from said leading edge and integrally joined to said sidewalls to define a first channel for channeling cooling air, and a second rib spaced from said first rib and integrally joined to said sidewalls to define a second channel for channeling cooling air, and said second rib is spaced from said trailing edge to define a third channel for channeling cooling air, anda plurality of rows of film cooling flank holes extending through said pressure sidewall in flow communication with said second and third channels, and being inclined along said span at different slopes.