Method and apparatus for correcting distortion in gas turbine en

Details Method and apparatus for correcting distortion in gas turbine en Method and apparatus for correcting distortion in gas turbine en

1976-12-13

1978-05-09

Larson, Lowell A.

Metal deforming

With exposure of work to gas, vapor, mist, or modified...

291568B, 72191, 72364, 148130, B21K 304

Patent

active

040879968

ABSTRACT:
Gas turbine engine blades and single-die cavities are dynamically balanced on a rotor, transferred to a neutral atmosphere heated chamber and rotated. The centrifugal force distributes sufficient stress on both the blade's platform and airfoil to correct critical geometrical characteristics by creep forming in a relatively short time. The process is not affected by the blade surface irregularities, which cause die damage in conventional opposed-die forming due to high stress concentrations.

REFERENCES:
patent: 2299860 (1942-10-01), Stoody et al.
patent: 2510304 (1950-06-01), Ames

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