Rotor blade for a compressor or a gas turbine

Details Rotor blade for a compressor or a gas turbine Rotor blade for a compressor or a gas turbine

2008-07-15

2008-07-15

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

Reexamination Certificate

active

11206156

ABSTRACT:
Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.

REFERENCES:
patent: 5924699 (1999-07-01), Airey et al.
patent: 6171058 (2001-01-01), Stec
patent: 7214034 (2007-05-01), Giot 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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