An improved turbine engine component includes an annular array of airfoils which extend between inner and outer shroud rings. In order to accommodate thermal expansion of the airfoils, cavities are provided in one of the shroud rings. The cavities may be formed by moving a shroud ring under the influence of forces applied to the shroud ring by a gating system. The cavities which are formed in the shroud ring to accommodate thermal expansion of the airfoils may be open-ended, completely closed-ended or partially closed-ended. When a turbine engine component having cavities in an inner shroud ring is to be formed, molten metal in an outer shroud ring mold cavity is first solidified to firmly grip outer ends of the airfoils. The molten metal in an inner shroud ring mold cavity is then solidified. As the molten metal in the inner shroud ring mold cavity solidifies, the gating system contracts to pull the metal in the inner shroud ring mold cavity inwardly relative to the airfoils. Core material may be positioned at the ends of the airfoils to at least partially form the shroud ring cavities.
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Join date : 2010-12-03
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