Dust resistant platform blade

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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C416S09000A, C416S248000

Reexamination Certificate

active

11243378

ABSTRACT:
A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation.

REFERENCES:
patent: 4992025 (1991-02-01), Stroud et al.
patent: 5382135 (1995-01-01), Green
patent: 6155778 (2000-12-01), Lee et al.
patent: 6164913 (2000-12-01), Reddy
patent: 6171058 (2001-01-01), Stec
patent: 6341939 (2002-01-01), Lee
patent: 2005/0095129 (2005-05-01), Benjamin et al.
GE Aircraft Engines, “CF6-80C2 HPT Stage 2 Blade,” on sale and in public use in US more than one year before Aug. 31, 2004.
U.S. Appl. No. 11/035,866; filed Jan. 10, 2005; “Funnel Fillet Turbine Stage,” by Ching-Pang Lee et al.

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