Gas turbine engine wall
A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
1. A gas turbine engine wall comprising:
an inner surface and an opposing outer surface having at least one film cooling hole defined therein, wherein said at least one film cooling hole comprises an inclined inlet bore that extends from said inner surface and a pair of channels that diverge laterally from an outlet end of said inclined inlet bore, wherein said pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape, wherein said ridge begins at a location spaced at a distance from the outlet end and separates a pressurized air at the ridge and decreases in depth as said ridge extends towards said outer surface and wherein an inclination angle of said ridge is at least initially smaller than an inclination angle of the inlet bore and said ridge decreases in depth in an arcuate profile.
2. The wall in accordance with claim 1 , wherein at least one of said pair of channels comprises a floor that has a substantially rounded cross-sectional shape.
3. The wall in accordance with claim 1 , wherein at least one of said pair of channels have a width that is substantially similar to a diameter of said inclined inlet bore.
4. The wall in accordance with claim 1 , wherein said ridge comprises an edge defined at a floor of said pair of channels, said edge separated by a distance from the outlet end of said inclined inlet bore.
5. The wall in accordance with claim 1 , wherein said ridge comprises a substantially constant width.
6. The wall in accordance with claim 1 , wherein said pair of channels decrease in depth with a substantially constant incline from the outlet end of said inclined inlet bore towards said outer surface.
7. The wall in accordance with claim 1 , wherein said pair of channels have an inclination angle that is shallower than the inclination angle of said ridge.
8. A gas turbine engine wall comprising:
an inner surface and an opposing outer surface having at least one film cooling hole defined therein, wherein said at least one film cooling hole comprises an inclined inlet bore that extends from said inner surface and a pair of channels that diverge laterally from an outlet end of said inclined inlet bore, wherein said pair of channels have a substantially planar floor and are separated by a ridge to form a boomerang cross-sectional chapel wherein said ridge begins at a location spaced at a distance from the outlet end and separates a pressurized air at the ridge and decreases in depth as said ridge extends towards said outer surface and wherein an inclination angle of said ridge is initially smaller than an inclination angle of the inlet bore and said inclination angle of said ridge changes over the length of the ridge in an arcuate profile.
9. The wall in accordance with claim 8 , wherein said substantially planar floor diverges in width from the outlet end of said inclined inlet bore towards a trailing edge of said pair of channels.
10. The wall in accordance with claim 8 , wherein said ridge decreases in depth with an increasing incline as said ridge extends towards said outer surface.
11. The wall in accordance with claim 8 , wherein said pair of channels comprise at least one side wall that extends from said substantially planar floor to said outer surface.
12. The wall in accordance with claim 11 , wherein said at least one side wall comprises a pair of side walls that extend from opposing edges of said substantially planar floor, said pair of side walls diverge from said substantially planar floor towards said outer surface.
13. The wall in accordance with claim 8 , wherein said pair of channels diverge at an angle of between about 20° to about 100°.
14. The wall in accordance with claim 8 , wherein said pair of channels are configured to divide and diffuse a flow of air discharged from said inclined inlet bore.