High pressure turbine disk hub with reduced axial stress and...

Details High pressure turbine disk hub with reduced axial stress and... High pressure turbine disk hub with reduced axial stress and...

2005-12-20

2009-08-25

Edgar, Richard (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Support mounting, carrier or fairing structure

C416S248000

Reexamination Certificate

active

07578656

ABSTRACT:
A gas turbine engine disk that includes a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a radially-displaced annular hub surface exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surface acts as an axial free surface mitigating the formation undesirable axial stress in the disk hub.

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patent: 7241111 (2007-07-01), Harding et al.
patent: 2112461 (1983-07-01), None

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