High pressure turbine disk hub with curved hub surface and...

Details High pressure turbine disk hub with curved hub surface and... High pressure turbine disk hub with curved hub surface and...

2005-12-20

2008-12-02

Nguyen, Ninh H (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Method of operation

C416S248000, C416S19800R

Reexamination Certificate

active

07458774

ABSTRACT:
A first stage turbine disk section for a gas turbine engine, including a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a convex, curved hub surface exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress.

REFERENCES:
patent: 5275534 (1994-01-01), Cameron et al.
patent: 5630703 (1997-05-01), Hendley et al.
patent: 5961287 (1999-10-01), Cairo
patent: 6375421 (2002-04-01), Lammas et al.
patent: 2112461 (1983-07-01), None

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