Sealing arrangement in a gas turbine engine

Details Sealing arrangement in a gas turbine engine Sealing arrangement in a gas turbine engine

2011-04-05

2011-04-05

Yu, Justine R (Department: 3745)

Rotary kinetic fluid motors or pumps

Bearing, seal, or liner between runner portion and static part

Dynamically created seal

C415S173300, C415S173700, C415S174200, C277S413000, C277S415000, C277S421000, C277S347000, C277S423000

Reexamination Certificate

active

07918643

ABSTRACT:
A compressor of a gas turbine engine comprises blades2, 4provided on blade platforms8, 12of a rotor. Stator vanes20lie between the blades2, 4and are connected to a vane support structure22. Sealing rings38are secured to the vane support structure22to restrict air flow into stator wells36on each side of the vane support structure22. The sealing rings38are made from a flexible material so that they deflect on installation of the vane support structure22in a direction radially inwards between the adjacent blade platforms8, 12.

REFERENCES:
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patent: 5328328 (1994-07-01), Charbonnel et al.
patent: 5890874 (1999-04-01), Lambert et al.
patent: 6514045 (2003-02-01), Barton et al.
patent: 7857582 (2010-12-01), Kovac et al.
patent: 0 926 314 (1999-06-01), None
patent: 780382 (1957-07-01), None
patent: A-2003-343206 (2003-12-01), None

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