Fluid reaction surfaces (i.e. – impellers) – Rotor having flow confining or deflecting web – shroud or... – Axially extending shroud ring or casing
Patent
1984-07-30
1986-06-17
Powell, Jr., Everette A.
Fluid reaction surfaces (i.e., impellers)
Rotor having flow confining or deflecting web, shroud or...
Axially extending shroud ring or casing
416248, F01D 530
Patent
active
045953406
ABSTRACT:
Disclosed is a bladed disk assembly having a new and improved rotor blade. The blade includes a shank and dovetail extending from an airfoil portion thereof. The shank includes a pocket extending therein from an end surface thereof. The shank pocket allows for reduced weight of the blade while maintaining acceptable bending stiffness thereof. In an exemplary embodiment of the invention, the bladed disk assembly is effective for being interchangeable with a blisk assembly having an inlet hub radius ratio of about less than about 0.5 and a root solidity of greater than about 2.2.
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General Electric, Aircraft Engine Business Group, Design Practice DP7004, Apr. 30, 1984, pp. 150 to 151.
Report AFAPL-TR-76-92, "Investigation of . . . Compressor with Low Hub/Tip Ratio,"-A. J. Wennerstrom, et al., Oct. 1976; 8 selected pp. including iii, 34, 36 & 48.
Report AFAPL-TR-76-59, "Design of . . . Compressor with Low Hub/Tip Ratio,"-A. J. Wennertrom et al., Oct. 1976, cover page & p. 29.
Ballantyne Douglas B.
Klassen David D.
Conte Francis L.
General Electric Company
Lawrence Derek P.
Powell Jr. Everette A.
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