| 摘要 |
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.
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