Blade tip clearance system

Details Blade tip clearance system Blade tip clearance system

2011-05-10

2011-05-10

Collins, Timothy D (Department: 3644)

Rotary kinetic fluid motors or pumps

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

Between blade edge and static part

Reexamination Certificate

active

07938621

ABSTRACT:
A pressure actuated tip clearance system for a shroud structure of a gas turbine engine rotary stage includes an annular plenum chamber formed between an annular arrangement of a plurality of shroud liners on the inner circumference of the chamber and a generally cylindrical casing on the radially outer side, and, in use, a hot gas stream radially inwards of the shroud liners. Each shroud liner comprises a hollow box section comprising upstream and downstream walls, radially inner and outer walls, and side walls, the downstream and radially inner and outer walls being closed, the upstream wall having an air inlet aperture, and at least one of the side walls having at least one outlet aperture. The inlet aperture is in flow communication with a source of high pressure air at a pressure higher than that of the gas stream.

REFERENCES:
patent: 4551064 (1985-11-01), Pask
patent: 5088888 (1992-02-01), Bobo
patent: 5374161 (1994-12-01), Kelch et al.
patent: 5375973 (1994-12-01), Sloop et al.
patent: 5641267 (1997-06-01), Proctor et al.
patent: 5871333 (1999-02-01), Halsey
patent: 1484288 (1977-09-01), None
patent: A-2169962 (1986-07-01), None
patent: A-2313414 (1997-11-01), None

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