Blade for rectifier provided in low pressure compressor of booster of turbojet, in aircraft, has platform comprising reference frame for positioning blade in rectifier, where reference frame is placed on upper face of platform

摘要

The blade has an end forming a platform to be welded on a ring (102) of a rectifier. The platform comprises an upper face (203) that is visible after being welded on the ring. The platform comprises a reference frame for positioning the blade in the rectifier, where the reference frame is placed on the upper face of the platform. The reference frame includes two grooves (205, 206) intersecting with each other and marking elements located at distance of about 2.5 mm from periphery of the platform. An independent claim is also included for a method for controlling aligning of a blade in a rectifier of a turbojet.