Turbo machine shroud-to-rotor blade dynamic clearance control

Rotary kinetic fluid motors or pumps – Bearing – seal – or liner between runner portion and static part – Between blade edge and static part

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Details

4151731, 415 47, F01D 1108

Patent

active

056014023

ABSTRACT:
A clearance control arrangement for the rotor blade-to-stator shroud clearance in an aircraft engine or other turbo machine. The disclosed arrangements use large area piston-like structures located circumferential to the turbo machine and capable of operation from pressures developed within the machine. One disclosed arrangement incorporates static adjustment capability that can be disposed to provide symmetrical or asymmetrical clearances. The disclosed clearance control can be used as a fast-acting supplement or in lieu of other clearance control arrangements and is arranged to be actuated upon sensing the onset of rotor-to-stator collision pinch point conditions in the turbo machine.

REFERENCES:
patent: 3085398 (1963-04-01), Ingleson
patent: 3391904 (1968-07-01), Albert et al.
patent: 3966354 (1976-06-01), Patterson
patent: 3975901 (1976-08-01), Hallinger et al.
patent: 3982850 (1976-09-01), Jenkinson
patent: 4247247 (1981-01-01), Thebert
patent: 4679981 (1987-07-01), Guibert et al.
patent: 4696619 (1987-09-01), Lardellier
patent: 4804310 (1989-02-01), Fuller et al.

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