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1. 发明申请

US20160319681A1 TURBINE DOVETAIL SLOT HEAT SHIELD 审中-公开
标题翻译：涡轮DOVETAIL SLOT HEAT SHIELD
公开(公告)号：US20160319681A1
公开(公告)日：2016-11-03
申请号：US14702097
申请日：2015-05-01
申请人： General Electric Company
发明人： Richard William Jendrix , Christopher Thomas Schuppe , Christopher John Van Derven , Samuel Joseph Stoughton , Charles Thomas McMillan , John David Bibler
IPC分类号： F01D5/30 , F01D5/02 , F01D5/18
CPC分类号： F01D5/3007 , F01D11/02
摘要： Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.
摘要翻译：燃气涡轮发动机涡轮机叶片组件包括接合到叶片根部的中空翼型件，结合或附接到根部的底部表面的燕尾槽隔热屏蔽件，以及从隔热件的屏蔽出口开口到径向延伸穿过径向内端部的入口孔根。防护罩可以具有腿部，其从腿部向下延伸，并且具有从护罩底部向上延伸的体部，倾斜的上游端部，腿部的自由端比隔热罩底部长。法兰可以沿着自由端定位并结合到底面。身体，护罩底部和/或腿部可以是圆形的。圆盘包括形成在边缘中的多个燕尾槽，互补的多个涡轮机叶片，其通过根部可拆卸地保持在燕尾槽中，燕尾槽的槽底部周向延伸到轮辋内的盘柱之间。热屏蔽底部可以在槽底部径向间隔开。

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