Film cooling hole for turbine airfoil
AssigneeFlorida Turbine Technologies, Inc.
InventorGeorge Liang
Life of this patent
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Abstract
A turbine airfoil with a film cooling hole having a bell mouth shaped opening that has expansion in both the side walls and the downstream wall of from 15 to 25 degrees. The film cooling hole includes an expansion section formed with two long ribs and one short rib to form three inlets of equal cross sectional areas so that the flows into the three passages are the same. The short rib forms two middle passages to combine with two outer passages to form four exit passages for the film hole. The two side walls are curved outward in the stream-wise oriented film hole and have an expansion of from 0 to 5 degrees in the compound angled film hole.
Claims16
A film cooling hole for an air cooled turbine airfoil used in a gas turbine engine, the film cooling hole comprising:
- An inlet section forming a metering section for the film cooling hole;
- A diffusion section located downstream from the metering section;
- The diffusion section having a downstream wall and two side walls all with a positive expansion;
- The diffusion section including two long ribs forming three inlets of equal cross sectional flow area;
- and,
- The diffusion section including a short rib formed between the two long ribs, the short rib and the two long ribs forming two outlets.
Dependencies are inferred from the claim text.