Hybrid blade for a gas turbine

Details Hybrid blade for a gas turbine Hybrid blade for a gas turbine

1995-09-25

1997-08-12

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Laminated, embedded member or encased material

416241A, 416230, F01D 514

Patent

active

056558830

ABSTRACT:
A lightweight, impact-resistant gas turbine blade, such as an aircraft engine fan blade, includes attached-together first-metal and second-composite segments together defining an airfoil portion. The first segment includes entirely the suction side, leading edge, and trailing edge from the blade root to the blade tip and further includes partially the pressure side near the leading and trailing edges from the blade root to the blade tip. The second segment includes partially the pressure side from near the leading edge to near the trailing edge from the blade root to near the blade tip.

REFERENCES:
patent: 3637325 (1972-01-01), Morley
patent: 3695778 (1972-10-01), Taylor
patent: 3903578 (1975-09-01), Rothman
patent: 4118147 (1978-10-01), Ellis
patent: 4594761 (1986-06-01), Murphy et al.
patent: 4643647 (1987-02-01), Perry
patent: 5145320 (1992-09-01), Blake et al.
patent: 5295789 (1994-03-01), Daguet
patent: 5429877 (1995-07-01), Eylon

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