Gas turbine blade having areas of different densities
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United States of America Patent
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-
Nov 24, 1998
Grant Date -
N/A
app pub date -
Apr 25, 1997
filing date -
Apr 25, 1997
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A lightweight, impact-resistant gas turbine blade, such as an aircraft engine fan blade, includes a metallic airfoil portion with at least one surface recess containing a void volume having adjacent first and second regions. Filler material is placed in and bonded to the surface recess and generally completely fills the void volume. The filler material in the first region has a higher average modulus of elasticity than that of the filler material in the second region.
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