Partially-metallic blade for a gas turbine

Details Partially-metallic blade for a gas turbine Partially-metallic blade for a gas turbine

1995-09-25

1997-06-03

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Coating, specific composition or characteristic

416229R, 416230, F01D 514

Patent

active

056347715

ABSTRACT:
A lightweight, impact-resistant gas turbine blade, such as an aircraft engine fan blade, has a metal solid section, composite or structural/syntactic foam segments, and metal solid spars all attached together to define an airfoil portion. The solid section includes the leading edge, blade tip, and trailing edge. The segments together are bounded in part by the solid section near the leading edge, blade tip, and trailing edge. The solid spars separate and are attached to the segments.

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U.S. Patent Application Serial No. 08/257602, filed May 23, 1994 by Jan., Schilling entitled, "Unshrouded Blading for High Bypass Turbofan Engines".
Concurrently filed U.S. Patent Application RD-24620, by J.C. Schilling entitled "Hybrid Blade for a Gas Turbine".

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