Cooled turbine blade for a gas turbine engine

Details Cooled turbine blade for a gas turbine engine Cooled turbine blade for a gas turbine engine

1983-05-24

1985-02-19

Yuen, Henry C.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

416 96R, F01D 508

Patent

active

045002584

ABSTRACT:
A cooled turbine blade is provided with an aerofoil which tapers from root end to tip end so that the thicker root section provides greater resistance to detachment of the aerofoil. In order to provide effective cooling and light weight the aerofoil has a central `dead` cavity which extends from its root and part way up the aerofoil. Spanwise cooling passages bifurcate to pass between the cavity and the side walls in the relatively constant metal thickness thus provided.

REFERENCES:
patent: 3628885 (1971-12-01), Sidenstick et al.
patent: 4326833 (1982-04-01), Zelahy et al.
patent: 4364160 (1982-12-01), Eiswerth et al.

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