Turbine balance arrangement with integral air passage

Details Turbine balance arrangement with integral air passage Turbine balance arrangement with integral air passage

1987-10-27

1990-02-06

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

416144, F01D 510, F01D 518

Patent

active

048985147

ABSTRACT:
A gas turbine rotor includes a disk (50) with axial dovetail slots (64) and air cooled blades (52) having mating, but shortened dovetails (66). The axial flow path (68) so formed is blocked at the far end and is in fluid communication with the blade cooling passages. Balance weights (70) fit within the openings in a manner which does not interfere with the cooling airflow.

REFERENCES:
patent: 2613058 (1952-10-01), Atkinson
patent: 2843356 (1958-07-01), Hull, Jr.
patent: 3297302 (1967-01-01), Spears
patent: 3644058 (1972-02-01), Barnabei et al.
patent: 3853425 (1974-12-01), Scalzo et al.
patent: 3888601 (1975-06-01), Glassburn
patent: 4477226 (1984-10-01), Carreno
patent: 4505640 (1985-03-01), Hsing et al.

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