Method of and structure for enabling cooling of the engaging...

Details Method of and structure for enabling cooling of the engaging... Method of and structure for enabling cooling of the engaging...

2005-12-06

2005-12-06

Nguyen, Ninh H. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Method of operation

C416S09600A, C416S09700R, C416S248000

Reexamination Certificate

active

06971852

ABSTRACT:
A gas turbine engine turbine section includes a turbine disk (20) which carries a stage of turbine blades (22). The turbine blades (22) have fir tree roots (24) which locate in fir tree grooves (26) in the rim of disk20. Some of the projections that form the fir tree roots (24) of blades (22) and fir tree grooves (26) of disk (20) are truncated so as to define spaces between their truncated surfaces and the roots between adjacent overlapping projections, thus enabling the passing of a cooling air flow therethrough.

REFERENCES:
patent: 2848193 (1958-08-01), Sells et al.
patent: 3501249 (1970-03-01), Scalzo et al.
patent: 1 076 446 (1960-02-01), None
patent: 1 209 419 (1970-10-01), None

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