Gas turbine rotor blade

Details Gas turbine rotor blade Gas turbine rotor blade

1998-12-01

2000-08-08

Verdier, Christopher

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

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

416191, 416192, F01D 518

Patent

active

060992530

ABSTRACT:
A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane direction so as to communicate with the first cooling holes, and is constructed such that the cooling gas can flow in a uniform distribution. The plurality of the first cooling holes 3 for flow of the cooling gas are bored in the blade portion 2 and the plurality of the second cooling holes 5 for flow of the cooling gas are bored in the shroud 1 along its plane direction. The second cooling holes 5 communicate with the first cooling holes 3, hole to hole, via two-step holes 4, and the second cooling holes 5 are bored alternately on the dorsal side and the ventral side of the rotor blade.

REFERENCES:
patent: 3164367 (1965-01-01), Lynch
patent: 4127358 (1978-11-01), Parkes
patent: 5460486 (1995-10-01), Evans et al.
patent: 5482435 (1996-01-01), Dorris et al.
patent: 5779447 (1998-07-01), Tomita et al.
patent: 5785496 (1998-07-01), Tomita
Patent Abstracts of Japan, vol. 1996, No. 12, Dec. 26, 1996.

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