Thermally-tuned rotary labyrinth seal with active seal clearance

Rotary kinetic fluid motors or pumps – Bearing – seal – or liner between runner portion and static part – Between axial flow runner and vane or vane diaphragm structure

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4151745, 277 3, 277 53, 277 75, F01D 1100

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active

052810909

ABSTRACT:
A thermally-tuned rotary labyrinth seal for a gas turbine engine includes an inner annular seal member having axially spaced, radially projecting annular seal teeth, and an outer annular seal member having a stepped honeycomb structure which face the annular seal teeth of the inner seal member and define therewith axially spaced regions bounded by the seal teeth and honeycomb structure. The seal teeth and stepped honeycomb structure cooperate to inhibit gas flow from one region to the next. Also, the seal has inlet and outlet vent holes defined through the honeycomb structure at respective upstream and downstream ends thereof which communicate with correspondingly located ones of the regions. The inlet and outlet vent holes are aligned along respective planes extending radially relative to a longitudinal axis of the engine and the holes are disposed at angles extending in tangential directions along the radial planes. Further, the seal includes an annular housing attached on an outer side of the honeycomb structure which defines a single axially elongated annular cavity spanning the honeycomb structure. The cavity interconnects in flow communication the inlet and outlet vent holes for providing gas flow in heat transfer relationship along the outer side of the honeycomb structure from the inlet vent holes to the outlet vent holes to provide active seal clearance control.

REFERENCES:
patent: 4513975 (1985-04-01), Hauser et al.
patent: 4526508 (1985-07-01), Antonellis et al.
patent: 4662821 (1987-05-01), Kervistin et al.
patent: 4668163 (1987-05-01), Kervistin

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