发明名称 Hollow rotor blade for the turbine of a gas turbine engine
摘要 The invention relates to a hollow blade comprising an internal cooling passage (24), an open cavity (30) located at the tip (14) of the blade and bounded by an end wall (26) and a rim (28) and cooling channels (32) that connect the said internal cooling passage (24) to the outer face of the pressure wall (16), the said cooling channels (32) being inclined to the pressure wall (16) in such a way that they emerge on the outer face of the pressure wall (16) near the top (28a) of the said rim. By way of feature, a reinforcement of material (34) is present between the rim (28) and the end wall (26) of the cavity (30) along at least one portion of the pressure wall (16), whereby the said rim (28) is widened at its base adjacent to the said end wall (26) in such a way that the cooling channels (32) emerge near the top (28a) of the rim (28) without reducing the mechanical strength of the tip (14) of the blade.
申请公布号 US2005063824(A1) 申请公布日期 2005.03.24
申请号 US20040909360 申请日期 2004.08.03
申请人 SNECMA MOTEURS 发明人 BOURY JACQUES;JUDET MAURICE
分类号 F01D5/18;F01D5/20;(IPC1-7):B63H1/14 主分类号 F01D5/18
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