| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a gas turbine engine with a fan, which prevents blocking of spaces between fan vanes by ice in an icing environment, while preventing the deterioration of aerodynamic performance of the fan in a non-icing environment. <P>SOLUTION: The gas turbine engine is located on the upstream side to a plurality of circularly arranged fan vanes and has a patterning area R which is patterned by coating areas R1 covered with an anti-icing coating and exposed areas R2 not covered with the anti-icing coating. In a view from the direction of chords of the fan vanes, a vane-side end R1a that is the fan vane side end of the coating area R1 is situated between the front edges of fan vanes adjacent to each other and has a width smaller than a space between the front edges. <P>COPYRIGHT: (C)2012,JPO&INPIT |
