Gas turbine airfoil leading edge cooling construction

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

Reexamination Certificate

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Reexamination Certificate

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10956096

ABSTRACT:
A gas turbine airfoil with a pressure sidewall (6) and a suction sidewall (7) extends from a root (2) to a tip (3) and from a leading edge (4) to a trailing edge (5). It comprises several film cooling holes with exit ports (8). The film cooling holes have a sidewall that is diffused in the direction of the tip (3) of the airfoil (1) at least over a part of the film cooling hole. Furthermore, the film cooling holes each have flare-like contour near the outer surface of the leading edge (4). The film cooling holes according to the invention provide an improved film cooling effectiveness due to reduced formation of vortices and decreased penetration depth of the cooling air film.

REFERENCES:
patent: 4684323 (1987-08-01), Field
patent: 4738588 (1988-04-01), Field
patent: 5779437 (1998-07-01), Abdel-Messeh et al.
patent: 6183199 (2001-02-01), Beeck et al.
patent: 0 924 384 (1999-06-01), None

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