Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Radial flow devices
Patent
1983-12-12
1986-04-29
Powell, Jr., E. A.
Fluid reaction surfaces (i.e., impellers)
Specific blade structure
Radial flow devices
416242, 416DIG2, 415181, F01D 514
Patent
active
045853959
ABSTRACT:
The invention comprises a blade for a gas turbine engine including an airfoil portion having a non-linear stacking axis intersecting a reference radial axis that is effective for generating a compressive component of bending stress due to centrifugal force acting on the blade. The compressive component of bending stress is provided in a life-limiting section of the blade, which, for example, includes trailing and leading edges of the blade. Inasmuch as the stacking axis, which represents the locus of centers of gravity of transverse sections of an airfoil portion of the blade, is non-linear, an increased amount of a compressive, component of bending stress can be generated at a life-limiting section between a root and tip of the blade without substantially increasing bending stress at the root of the blade due to the non-linear stacking.
REFERENCES:
patent: 2660401 (1953-11-01), Hull
patent: 2663493 (1953-12-01), Keast
patent: 2715011 (1955-08-01), Schorner
patent: 2915238 (1959-12-01), Szydlowski
patent: 3333817 (1967-08-01), Rhomberg
patent: 3851994 (1974-12-01), Seippel
patent: 3989406 (1976-11-01), Bliss
patent: 4012172 (1977-03-01), Schwaar et al.
patent: 4284388 (1981-08-01), Szewalski
patent: 4460315 (1984-07-01), Tseng
Aviation Wk. & Space Technology--May 2, 1983, Howmet advertisement.
F404 LP Turbine Aeromechanical Summary, Feb. 12, 1976, V. M. Cardinale and R. A. McKay, four-page extract.
Abbott David R.
Bourneuf John J.
Nourse John G.
Conte Francis L.
General Electric Company
Lawrence Derek P.
Powell, Jr. E. A.
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