Turbine nozzle with sloped film cooling

Details Turbine nozzle with sloped film cooling Turbine nozzle with sloped film cooling

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01) F01D 9/02 (2006.01)

Patent

CA 2327857

A turbine nozzle vane (18) includes pressure and suction sidewalls (26,28) extending between leading and trailing edges (34,36). The vane includes a pair of integral ribs (38,40) defining three internal cooling channels (42-46) between the leading and trailing edges. Rows of film cooling holes (1-13) extend through the sidewalls, and three rows (8-10) in the pressure side are inclined along the span of the airfoil at different slopes.

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