Gas turbine rotor

Fluid reaction surfaces (i.e. – impellers) – Multiple axially spaced working members – Differing radii

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Details

416244A, 416248, F01D 506

Patent

active

058607897

ABSTRACT:
A gas turbine has a gas turbine rotor including a plurality of rotary disks each having an opening of a circular shape formed through its central portion, the rotary disk including a pair of hub portions formed respectively on opposite sides thereof, and a pair of in-low portions formed respectively at the opposite sides thereof. The gas turbine rotor also includes a plurality of spacers each having an opening of a circular shape formed through its central portion, the spacer having a pair of in-low portions formed respectively at opposite sides thereof. The rotary disks and the spacers are alternately stacked together in such a manner that the opposite sides of each of the spacers contact opposed side surfaces of the adjacent hub portions, respectively, and that the in-low portions of each of the spacers are engaged respectively with the in-low portions of the adjacent rotary disks. The stack of rotary disks and spacers are fastened together in an axial direction by stacking bolts. A thickness of that portion of the rotary disk extending radially from an inner periphery of the hub portions to an inner peripheral surface of the rotary disk is so determined that stresses, developing at the inner peripheral surface of the rotary disk, can be made generally equal to one another over an entire area thereof.

REFERENCES:
patent: 4784572 (1988-11-01), Novotny et al.
patent: 4844694 (1989-07-01), Naudet
patent: 4880354 (1989-11-01), Teranishi et al.
patent: 4901523 (1990-02-01), Huelster
patent: 5054996 (1991-10-01), Carreno
"The prototype-Tested 3A-Series Gas Turbines", pp. I-283 to 289, 95-Yokohama IGTC-145, Presented at 1995 Yokohama International Gas Turbine Congress held Oct. 22, 1995-Oct. 27, 1995.

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