Film cooling hole for turbine airfoil

Details Film cooling hole for turbine airfoil Film cooling hole for turbine airfoil

2008-10-16

2011-11-15

Chaudhari, Chandra (Department: 2891)

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

C415S115000

Reexamination Certificate

active

08057179

ABSTRACT:
A film cooling hole for a turbine airfoil used in a gas turbine engine, where the film cooling hole includes an expansion section with a downstream side wall having a first expansion in the middle section and a second expansion greater than the first expansion in the two corners of the downstream side wall. The corners with a greater expansion seal off hot gas ingestion between the film flow and the airfoil surface immediately downstream from the hole opening which minimize the vortices' formation and thus improve the film effectiveness level. The film cooling hole includes two side walls with an expansion of around 10 degrees and an upstream side wall with no expansion. An inlet to the diffusion section includes a metering section of constant diameter to meter cooling air flow.

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patent: 6869268 (2005-03-01), Liang
patent: 6918742 (2005-07-01), Liang

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