Centrifugal compressor provided with a marker for measuring wear and a method of monitoring wear using said marker
A device and method for precise measurement of erosion of compressors, without removing an engine, and with easy positioning. A 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. The casing, covered with an abradable coating, includes an annular elbow zone in a substantially median part. Marking depressions of predetermined depths, preferably in groups, 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. Erosion occurs in the elbow of the casing and evolution thereof may enable monitoring of erosion of other components of the compressor, in particular the blades of the impeller.
1. A centrifugal compressor of a gas turbine with a radial air inlet, comprising:
an impeller including vanes; and
a casing for delimiting a flow of an air stream in the vanes, a central part of the casing including an annular zone forming an elbow,
wherein the casing is covered with an abradable coating,
wherein a marking depression of a predetermined depth as a marker is machined in the abradable coating in the annular zone forming the elbow, the marker includes a face and walls connecting a surface of the abradable coating to the face of marker, and a distance between the surface of the abradable coating and the face of the marker is equal to the predetermined depth,
wherein the casing includes two groups, each group including two markers, the groups of markers being distributed along the annular zone forming the elbow of the casing, the groups of markers being distributed at a predetermined distance from each other, and
wherein the markers of each group have different and quantified predetermined depths.
2. A centrifugal compressor according to claim 1 , wherein the markers of each group are aligned in the annular zone forming the elbow, and installation of the markers of each group is chosen between a meridian, a radius, and a line inclined between the meridian and the radius.
3. A centrifugal compressor according to claim 2 , wherein the markers of a same group are less than 10 mm apart to be configured to undergo a same type of erosion.
4. A centrifugal compressor according to claim 1 , wherein the marker has a maximum aperture of less than 1 mm so as not to be blocked by ingestion of foreign bodies, or ingestion of grains of sand.
5. A centrifugal compressor according to claim 1 , wherein the marker has a shape chosen from among a cylindrical shape, or a bore with a base which is circular or oblong, a spherical segment, a conical shape, and a grooving.
6. A method of monitoring wear on a centrifugal compressor, the method comprising:
providing a casing with a central part of the casing including an annular zone forming an elbow, the casing being covered with an abradable coating;
producing at least two markers by machining depressions of a predetermined depth in the abradable coating of the annular zone forming the elbow of the casing, each of the at least two markers including a face and walls connecting a surface of the abradable coating to the face of each of the markers, and a distance between the surface of the abradable coating and the face of the marker is equal to the predetermined depth;
performing examinations by endoscopy successively over time;
introducing, for each examination, an endoscope into the compressor, and positioning an active end of the endoscope facing each of the at least two markers to provide an image signal of each of the at least two markers;
processing the image signal to determine a number of remaining markers; and
applying a criterion for decision on removing the engine based on the number of remaining markers and comparative wear data,
wherein the markers have different depths and a difference between closest two depths is determined according to a calibrated degree of advance of wear.
7. A method of monitoring wear according to claim 6 , wherein the markers are distributed over a circumference of the annular zone forming the elbow of the casing at a predetermined distance from each other.
8. A method of monitoring wear according to claim 6 , wherein a comparison between the number of remaining markers during successive examinations supplies a measurement of a speed of erosion and progress of wear on the casing and other parts of the compressor, based on extrapolating stored data relating to correlations of wear between parts of the compressor.
9. A method of monitoring wear according to claim 8 , wherein for each examination, the decision criterion compares the number of remaining markers with a critical number established as a function of stored data, and an engine is removed for replacement of the worn parts when the critical number is reached.