Gas turbine rotor support systems

Details Gas turbine rotor support systems Gas turbine rotor support systems

1980-03-31

1981-12-22

Artis, Henry K.

Cutlery

308188, 308191, 308207R, F16C 1300, F16C 3300, F16C 3500

Patent

active

043067557

ABSTRACT:
A rotor assembly, particularly for a gas turbine engine, comprising a torsionally stiff drive shaft 16 mounted at two spaced locations in first and second bearings 22,23 which are substantially immovable bodily in radial directions. The drive shaft 16 has a flexible end portion 15 constituted by a shaft 25, projecting beyond the first bearing 23 which is more flexible in bending than the span of the drive shaft 16 between the first and second bearings 22,23. A support means 27 is mounted for rotation in a third bearing 28. The rotor 11 is mounted on the flexible end portion 15 of the drive shaft 16 to be driven thereby and is also mounted on the support means 27 for rotation in the third bearing 28. The third bearing 28 is capable of accommodating radial deflections of the support means 27 when the rotor becomes unbalanced.

REFERENCES:
patent: 2390353 (1945-12-01), Boysky
patent: 3446542 (1969-05-01), Whitehurst
patent: 3484144 (1969-12-01), Nash
patent: 3491536 (1970-01-01), Hadaway

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