| 摘要 |
The turbine paddle, for the rotor of a gas turbine motor e.g. an aircraft engine, has a point and an upstream entry edge (18) and a downstream exit edge (20) with flats (34,36). The paddle profile has a depth parallel to the flow direction, and a profile thickening (D) parallel to the running direction. An abrasive coating (22) is applied to the paddle point to act on a wear coating in the surrounding housing, with a length (DA) at the edges at least equal to or longer than a set minimum (DA,min).
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