Gas turbine or compressor blade

Details Gas turbine or compressor blade Gas turbine or compressor blade

2005-08-18

2008-12-02

Kershteyn, Igor (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

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

Axially extending shroud ring or casing

C416S191000, C416S19300A

Reexamination Certificate

active

07458779

ABSTRACT:
A gas turbine or compressor blade, includes a convex outer surface or suction side and a concave inner surface or pressure side, these sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases and terminating on a platform, one part of which includes a downstream fairing that includes at least one through-notch that extends substantially between a transverse line passing through the trailing edge and the downstream end of the fairing.

REFERENCES:
patent: 835473 (1906-11-01), Rotter
patent: 4365933 (1982-12-01), Langer et al.
U.S. Appl. No. 11/206,156, filed Aug. 18, 2005, Bil et al.
U.S. Appl. No. 11/206,155, filed Aug. 18, 2005, Bil et al.

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