FIELD: engines and pumps.
SUBSTANCE: centrifugal compressor of a gas turbine with a radial air inlet includes an impeller including blades and a casing for an air stream to flow in the blades of the impeller. Casing, covered with an abradable coating, includes an annular elbow zone in a substantially median part. Marking depressions (M1–M3) of predetermined depths, preferably in groups (G1, G2), are machined in the abradable coating of the zone. Examinations by endoscopy are successively performed to provide an image signal of the markers. Processing the endoscopic signal supplies a number of remaining markers and a criterion for decision on removing the engine is applied thereto.
EFFECT: invention is aimed at accurate measurement of compressor erosion without dismantling of an engine, as well as simple installation.
12 cl, 6 dwg
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