Patent ID: 8533947
Filing Date: 2013-09-17
Classification: B33Y,F01D,F05D,Y10T

Abstract:
1. A method of forming a turbine engine component having a plurality of airfoils disposed in an annular array between inner and outer shroud rings, said method comprising the steps of forming an inner shroud ring pattern by sequentially forming cross sectional layers of the inner shroud ring pattern and interconnecting the cross sectional layers of the inner shroud ring pattern, forming an outer shroud ring pattern by sequentially forming cross sectional layers of the outer shroud ring pattern and interconnecting the cross sectional layers of the outer shroud ring pattern, positioning at least an annular portion of the inner shroud ring pattern and at least an annular portion of the outer shroud ring pattern in a coaxial relationship, thereafter, positioning a plurality of airfoils in an annular array with radially inner end portions of the airfoils adjacent the inner shroud ring pattern and radially outer end portions of the airfoils adjacent the outer shroud ring pattern, covering the inner and outer shroud ring patterns with ceramic mold material, removing the inner and outer shroud ring patterns from the covering of ceramic mold material to leave inner and outer shroud ring mold cavities having configurations corresponding to the configurations of the inner and outer shroud ring patterns, filling the inner and outer shroud ring mold cavities with molten metal, and solidifying the molten metal in the inner and outer shroud ring mold cavities to form inner and outer shroud rings which are connected to the radially inner and outer end portions of the airfoils.