Gas turbine engine rotor disc with cooling fluid passage

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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415115, 415116, 416219R, 416 95, F01D 508

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active

058880496

ABSTRACT:
A gas turbine engine rotor disc (20) is provided with a plurality of cooling air supply passages (32) which are generally radially extending but are inclined in the downstream direction. Each passage (32) has a cross-sectional configuration which renders the ends (34) of the passages (32) less likely than normal to act as the site of hoop-stress induced cracks.

REFERENCES:
patent: 3014269 (1961-12-01), Graham et al.
patent: 3918835 (1975-11-01), Yamarik et al.
patent: 4344738 (1982-08-01), Kelly et al.
patent: 4626169 (1986-12-01), Hsing et al.
patent: 4923371 (1990-05-01), Ben-Amoz
patent: 5700130 (1997-12-01), Barbot et al.

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