Device for tuning clearance in a gas turbine, while...

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

Reexamination Certificate

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Details

C415S136000, C415S175000, C415S178000

Reexamination Certificate

active

11072534

ABSTRACT:
A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to discharge air onto the casing in order to modify the temperature thereof. A tubular air manifold is disposed around the air flow duct(s). There are also disposed an air feed tube to supply the tubular air manifold with air and an air pipe opening in the tubular air manifold and opening out into the air flow duct(s). The air pipe is provided with a balancing diaphragm for balancing the air flowing through the pipe.

REFERENCES:
patent: 4849895 (1989-07-01), Kervistin
patent: 5100291 (1992-03-01), Glover
patent: 6149074 (2000-11-01), Friedel et al.
patent: 6896038 (2005-05-01), Arilla et al.
patent: 0 492 865 (1992-07-01), None
patent: 0 541 325 (1993-05-01), None
patent: 0 892 152 (1999-01-01), None
patent: 0 892 153 (1999-01-01), None
patent: 1 205 637 (2002-05-01), None
patent: 2 652 858 (1991-04-01), None

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