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.

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. 112-. (canceled)13. A centrifugal compressor of a gas turbine with a radial air inlet , comprising:an impeller including vanes and a casing for flow of the air stream in the vanes,wherein the casing is covered with an abradable coating and includes an annular elbow zone in a substantially median part in which at least one marking depression of a predetermined depth as a marker is machined in the abradable coating.14. A centrifugal compressor according to claim 13 , wherein at least two claim 13 , or at least three groups of at least two claim 13 , or at least three markers claim 13 , are distributed regularly along the elbow zone of the casing.15. A centrifugal compressor according to claim 13 , wherein the markers of each group have different and quantified initial depths.16. A centrifugal compressor according to claim 13 , wherein the markers of each group are aligned in the elbow zone and installation thereof is chosen between a meridian claim 13 , a radius claim 13 , and a line inclined between the meridian and the radius.17. A ...

HELICOPTER ENGINE AIR INTAKE WITH INCREASED BYPASS FLOW

A helicopter engine air intake including an anti-icing grid that provides a large bypass flow in event of icing. The air intake includes air intake lips and an anti-icing grid mounted on outer ends of the air intake lips, being interposed in the air flow penetrating into the air intake, at least one air intake lip being formed by a thin metal sheet. 110-. (canceled)11. An air intake for a gas turbine helicopter engine including a compressor and a passage for feeding the compressor with air , which passage opens out at its upstream end via the air intake , the air intake comprising:air intake lips; andan anti-icing grid mounted on outer ends of the air intake lips, being interposed in an air flow penetrating into the air intake;wherein at least one air intake lip is formed by a thin metal sheet.12. An air intake according to claim 11 , wherein the thin metal sheet forming the at least one air intake lip possesses thickness of less than 1.5 mm claim 11 , or of less than 0.8 mm.13. An air intake according to claim 11 , wherein an outer end of the at least one air intake lip has a U-shaped curve claim 11 , and a margin of the anti-icing grid is engaged in the U-shaped space.14. An air intake according to claim 11 , wherein a margin of the anti-icing grid includes fastener tabs that are fastened to the at least one air intake lip.15. An air intake according to claim 11 , wherein a margin of the anti-icing grid includes a continuous fastener bead fastened to the at least one air intake lip.16. An air intake according to claim 11 , wherein a margin of the anti-icing grid is fastened to the at least one air intake lip by welds.17. An air intake according to claim 11 , wherein fastening of the anti-icing grid to the at least one air intake lip is devoid of adhesive bonding.18. An air intake according to claim 11 , wherein a margin of the anti-icing grid is a part that is separate from a body of the anti-icing grid claim 11 , the margin of the grid being fastened to the body ...

AIR INLET FOR HELICOPTER ENGINE WITH INCREASED BYPASS CIRCULATION

CENTRIFUGAL COMPRESSOR EQUIPPED WITH A WEAR MEASUREMENT MARKER AND WEAR FOLLOWING METHOD USING THE MARKER

L'invention vise à réaliser une mesure précise de l'érosion des compresseurs, sans dépose moteur, ainsi qu'une mise en place aisée. Pour ce faire, il a été remarqué que l'érosion se produit dans le coude du couvercle et son évolution peut alors permettre de suivre l'érosion d'érosion des autres pièces du compresseur, en particulier les pales du rouet. De manière générale, un compresseur centrifuge (1) de turbine à gaz à entrée d'air radiale comporte notamment un rouet, équipé de pales et un couvercle (12) d'écoulement de flux d'air dans les pales du rouet. Le couvercle (12), recouvert d'un revêtement abradable, présente une zone annulaire (120, 121) de coude (12a) dans une partie sensiblement médiane. Dans le revêtement abradable de cette zone (12a, 120), ont été usinés des creux de marquage (M1 à M3) de profondeurs déterminées, de préférence en groupes (G1, G2). Des examens par endoscopie sont successivement effectués pour fournir un signal d'image des marquages. Un traitement du signal endoscopique fournit un nombre de marquage(s) restant(s) et un critère de décision de dépose moteur lui est appliqué. The invention aims to achieve a precise measurement of the erosion of compressors, without engine removal, and easy implementation. To do this, it has been noticed that erosion occurs in the elbow of the cover and its evolution can then make it possible to follow the erosion erosion of the other parts of the compressor, in particular the impeller blades. In general, a radial air compressor centrifugal compressor (1) with radial air inlet comprises in particular a wheel, equipped with blades and a cover (12) for flow of air in the impeller blades. The cover (12), covered with an abradable coating, has an annular zone (120, 121) of elbow (12a) in a substantially median portion. In the abradable coating of this zone (12a, 120), marking hollows (M1 to M3) of predetermined depths, preferably in groups (G1, G2), have been ...

AIR INLET FOR HELICOPTER ENGINE WITH INCREASED BYPASS CIRCULATION

Entrée d'air pour moteur d'hélicoptère munie d'une grille antigivrage offrant une circulation de contournement importante en cas de givrage. Selon l'invention, cette entrée d'air comprend des lèvres d'entrée d'air (30, 32), et une grille anti-givrage (36) montée sur des extrémités externes (30a, 32a) des lèvres d'entrée d'air (30, 32) et s'interposant dans la circulation d'air pénétrant dans l'entrée d'air (34), au moins une lèvre d'entrée d'air (30, 32) étant formée par une tôle métallique fine. Air intake for helicopter engine equipped with an anti-icing grid providing significant bypass circulation in case of icing. According to the invention, this air inlet comprises air inlet lips (30, 32), and an anti-icing grid (36) mounted on external ends (30a, 32a) of the inlet lips of air (30, 32) and interposed in the flow of air entering the air inlet (34), at least one air inlet lip (30, 32) being formed by a metal sheet fine.

Helicopter engine air intake with increased bypass flow

A helicopter engine air intake including an anti-icing grid that provides a large bypass flow in event of icing. The air intake includes air intake lips and an anti-icing grid mounted on outer ends of the air intake lips, being interposed in the air flow penetrating into the air intake, at least one air intake lip being formed by a thin metal sheet.

Centrifugal compressor provided with a marker for measuring wear and a method of monitoring wear using said marker

L'invention vise à réaliser une mesure précise de l'érosion des compresseurs, sans dépose moteur, ainsi qu'une mise en place aisée. Pour ce faire, il a été remarqué que l'érosion se produit dans le coude du couvercle et son évolution peut alors permettre de suivre l'érosion d'érosion des autres pièces du compresseur, en particulier les pales du rouet. De manière générale, un compresseur centrifuge (1) de turbine à gaz à entrée d'air radiale comporte notamment un rouet, équipé de pales et un couvercle (12) d'écoulement de flux d'air dans les pales du rouet. Le couvercle (12), recouvert d'un revêtement abradable, présente une zone annulaire (120, 121 ) de coude (12a) dans une partie sensiblement médiane. Dans le revêtement abradable de cette zone (12a, 120), ont été usinés des creux de marquage (M1 à M3) de profondeurs déterminées, de préférence en groupes (G1, G2). Des examens par endoscopie sont successivement effectués pour fournir un signal d'image des marquages. Un traitement du signal endoscopique fournit un nombre de marquage(s) restant(s) et un critère de décision de dépose moteur lui est appliqué.

Centrifugal compressor provided with a marker for measuring wear and a method of monitoring wear using said marker

L'invention vise à réaliser une mesure précise de l'érosion des compresseurs, sans dépose moteur, ainsi qu'une mise en place aisée. Pour ce faire, il a été remarqué que l'érosion se produit dans le coude du couvercle et son évolution peut alors permettre de suivre l'érosion d'érosion des autres pièces du compresseur, en particulier les pales du rouet. De manière générale, un compresseur centrifuge (1) de turbine à gaz à entrée d'air radiale comporte notamment un rouet, équipé de pales et un couvercle (12) d'écoulement de flux d'air dans les pales du rouet. Le couvercle (12), recouvert d'un revêtement abradable, présente une zone annulaire (120, 121 ) de coude (12a) dans une partie sensiblement médiane. Dans le revêtement abradable de cette zone (12a, 120), ont été usinés des creux de marquage (M1 à M3) de profondeurs déterminées, de préférence en groupes (G1, G2). Des examens par endoscopie sont successivement effectués pour fournir un signal d'image des marquages. Un traitement du signal endoscopique fournit un nombre de marquage(s) restant(s) et un critère de décision de dépose moteur lui est appliqué.

CENTRIFUGAL COMPRESSOR EQUIPPED WITH A WEAR MEASUREMENT MARKER AND WEAR FOLLOWING METHOD USING THE MARKER

The aim of the invention is to take an accurate measurement of the erosion of compressors, without removal of the engine, and to provide for simple installation. For this purpose, it has been observed that erosion takes place in the elbow of the cover and the progress of said erosion can thus enable the monitoring of erosion to the other parts of the compressor, in particular the blades of the impeller. Generally, a centrifugal compressor (1) of a gas turbine with a radial air inlet comprises, in particular, an impeller provided with blades and a cover (12) for the flow of air through the impeller blades. The cover (12) is covered with an abradable coating and has an annular area (120, 121) of the elbow (12a) in a substantially median portion. Hollow markings (M1 to M3) of determined depths have been machined in the abradable coating of this area (12a, 120), preferably in groups (G1, G2). Endoscopic examinations are carried out successively to provide an image signal of the markings. Endoscopic signal processing provides a number of remaining markings and a decision criterion for removing the engine is applied to same.