Gas turbine blade retention

Fluid reaction surfaces (i.e. – impellers) – Rotor having flow confining or deflecting web – shroud or... – Axially extending shroud ring or casing

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Details

416221, 2988921, F01D 526

Patent

active

055183697

ABSTRACT:
Gas turbine blades 14 are slid axially into disc 12 with a retention tang 22 on each abutting the disc. An axially extending space 28 between blade platforms 26 and the disc receives elongated strip 30. With prebent end 34 resiliently held against the disc the opposite end 36 is bent radially outward against the roots of adjacent blades. A bow 38 biases the blades outwardly, deterring vibration.

REFERENCES:
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patent: 2942842 (1960-06-01), Hayes
patent: 3248081 (1966-04-01), Bobo et al.
patent: 4029436 (1977-06-01), Shoup, Jr. et al.
patent: 4457668 (1984-07-01), Hallinger
patent: 4483661 (1984-11-01), Manharth et al.
patent: 4730983 (1988-03-01), Naudet et al.
patent: 4872810 (1989-10-01), Brown et al.
patent: 5281097 (1994-01-01), Wilson et al.

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