Cooled turbine spar shell blade construction

Fluid reaction surfaces (i.e. – impellers) – With fluid passage in working member communicating with... – Discharge solely at periphery normal to rotation axis

Reexamination Certificate

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Details

C416S09600A, C416S09700R

Reexamination Certificate

active

07080971

ABSTRACT:
A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a tip portion extending in the spanwise direction and extending beyond the first wall and the second wall and a root portion extending longitudinally, an attachment portion having a central opening for receiving the root portion and a platform portion. The root portion fits into the central opening and is secured therein by a pin extending transversely through the attachment and the root portion. The shell fits over the spar and is supported thereto by a plurality of complementary hooks extending from the spar and shell. The ends of the shell fit into grooves formed on the tip portion and the platform.

REFERENCES:
patent: 4257737 (1981-03-01), Andress et al.
patent: 4321010 (1982-03-01), Wilkinson et al.
patent: 4473336 (1984-09-01), Coney et al.
patent: 4563125 (1986-01-01), Boudigues et al.
patent: 4753575 (1988-06-01), Levengood et al.
patent: 5476364 (1995-12-01), Kildea
patent: 5700131 (1997-12-01), Hall et al.
patent: 6422819 (2002-07-01), Tsai et al.

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