Turbine rim cavity sealing

Details Turbine rim cavity sealing Turbine rim cavity sealing

2008-11-22

2011-10-18

Geyer, Scott B (Department: 2812)

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

C416S174000, C415S230000

Reexamination Certificate

active

08038399

ABSTRACT:
A rim cavity seal arrangement for a gas turbine engine, where the rim cavity is formed between two rotor disk stages with a stator vane assembly positioned between the rotor disks and extending into the rim cavity. A cover plate secured onto a side of the rotor disk includes a plurality of cooling air injectors directed to discharge cooling air into an annular groove formed on the underside of the vane endwall adjacent to the rotor disk to form an air cushion that seals the rim cavity from hot gas ingestion. The cover plate forms a cooling air supply passage with the rotor disk side to supply the injectors, and the cover plate includes at least one metering hole to meter the pressurized air into the injectors.

REFERENCES:
patent: 3009682 (1961-11-01), Johnson
patent: 4642024 (1987-02-01), Weidner
patent: 4752185 (1988-06-01), Butler et al.
patent: 5352087 (1994-10-01), Antonellis
patent: 5749701 (1998-05-01), Clarke et al.
patent: 6189891 (2001-02-01), Tomita et al.
patent: 6398488 (2002-06-01), Solda et al.
patent: 6899520 (2005-05-01), Habedank et al.
patent: 2008/0145208 (2008-06-01), Klasing et al.

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