| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a turbine frame assembly of a gas turbine engine. <P>SOLUTION: This turbine frame assembly of the gas turbine engine is an integrated metallic casting object having (a) a turbine frame 38 including (i) an outer ring 48, (ii) a hub 42 and (iii) a plurality of struts 54 extending between the hub 42 and the outer ring 48, (b) a two-part strut fairing 72 including (i) an inner band 82, (ii) an outer and 80 and (iii) a vane-like part-shaped vane 78 extending between the inner and outer bands and surrounding the respective struts 54, and (c) a plurality of nozzle segments 76 arranged between the outer ring 48 and the hub 42, wherein the respective nozzle segments 76 include (i) a bow-shaped outer band 148, (ii) a bow-shaped inner band 150 and (iii) a vane-like part-shaped vane 148. <P>COPYRIGHT: (C)2010,JPO&INPIT</p> |
