| 摘要 |
The invention relates to a rotation-locking device of a sector of rectifier blades ( 5 ) mounted in a sector of the turbojet housing. A sector of blades comprises a support base ( 3 ). A housing sector comprises two recesses perpendicular to the axis of the housing, each receiving an edge ( 34 - 1, 34 - 2 ) of the support base. At one and the same axial end of the housing sector, each recess opens out into a seat ( 30 - 1, 30 - 2 ) defining an axial face ( 32 - 1 ). The device comprises an axial stop ( 26 ) adapting itself on each side in the seats ( 30 - 1; 30 - 1 ) of the two recesses, and once the complementary sector of the housing is installed and during operation of the turbojet, bearing on the axial faces ( 32 - 1 ) under the thrust of the complementary sector of rectifier blades in order to provide rotation locking.
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