Skirted turbine blade

Details Skirted turbine blade Skirted turbine blade

2006-08-29

2006-08-29

Nguyen, Ninh H. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Rotor having flow confining or deflecting web, shroud or...

Axially extending shroud ring or casing

C416S239000

Reexamination Certificate

active

07097429

ABSTRACT:
A turbine blade includes an airfoil, platform, shank, and dovetail. The shank includes opposite forward and aft faces corresponding with leading and trailing edges of the airfoil, and opposite first and second sides corresponding with pressure and suction sides of the airfoil. The shank further includes lugs extending outwardly from the two sides, with a first lug having an inverted skirt extending outwardly toward the platform to join the shank aft face. The skirt cooperates with a seal body when mounted in the engine for reducing inter-blade leakage.

REFERENCES:
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patent: 0 913 556 (1999-05-01), None
patent: 2127104 (1984-04-01), None
patent: 2194000 (1988-02-01), None
GE Aircraft Engines, “Stage-two Turbine Blade,” in public use and on sale in USA and world before Jun. 1, 2003, 7 figures.

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