发明名称 Method of machining integral bladed rotors for a gas turbine engine
摘要 A method of manufacturing an integral bladed rotor is disclosed. The method includes calculating a cutting path in an area of a blank between adjacent blade locations to approximate contours of adjacent blades. A cutter is plunged into the area at an initial angle and depth that extends from an outer perimeter to the blank to an inner perimeter of the blank, in one example. The blade roots extend from the inner perimeter, and the blade tips terminate near the outer perimeter. The cutter is plunged into the area at an original angle that, in one example, is different than the initial angle. The cutter is rotated about an axis in a spiral-like fashion as the cutter extends further into the blank, along the cutting path.
申请公布号 US7967659(B2) 申请公布日期 2011.06.28
申请号 US20080120786 申请日期 2008.05.15
申请人 UNITED TECHNOLOGIES CORPORATION 发明人 ERICKSON ROBERT E.;FAUGHNAN, JR. PAUL R.
分类号 B24B49/00 主分类号 B24B49/00
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