Axial turbomachine compressor outer casing
The invention relates to a casing, particularly of an axial turbomachine compressor. This casing comprises a support of cylindrical overall shape made of composite material, a metal ring fitted by bonding to the internal surface of the support, and a layer of abradable material fitted by plasma spray onto the internal surface of the metal ring. The metal ring is preferably made of stainless steel and is preferably perforated. The perforation allows better keying of the adhesive and allows the degassing thereof. The external surface of the metal ring is preferably sandblasted prior to bonding. Its internal surface is also preferably sandblasted prior to the plasma spraying of the abradable material.
1. A method of manufacturing a shell of a compressor of an axial turbomachine, said method comprising the following steps:
providing a support of a composite material with an organic matrix having one of a generally ring-shaped and a generally cylindrical shape with a generally circular inner surface, the support being a structural element ensuring rigidity of the turbomachine;
fixing a metal ring on the support, the ring being a strip comprising a series of perforations distributed over its surface and having an inner surface and an outer surface opposite to the inner surface wherein the metal ring is fixed on the support by gluing the metal ring on an inner surface of the support; and
applying an abradable layer on the inner surface of the ring.
2. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein applying the abradable layer on the inner surface of the ring is performed by plasma spraying, and wherein the abradable material comprises AlSi polyester.
3. The method of manufacturing the shell of an axial turbomachine according to claim 1 further comprising a step of preparing the inner surface of the ring by one of sandblasting and chemical etching prior to applying the abradable layer on the inner surface of the ring.
4. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein the perforations have a diameter that is one of less than 1 mm and equal to 1 mm.
5. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein the ring comprises a wire mesh.
6. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein the metallic material of the ring is comprised of at least one of stainless steel, titanium, nickel-iron alloy and FeNi36.
7. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein the ring is made of a porous material.
8. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein the ring has a thickness between 0.1 mm and 1 mm.
9. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein the ring is made of a plurality of segments.
10. The method of manufacturing the shell of a compressor of an axial turbomachine according to claim 1 , wherein the adhesive layer is in direct contact with the inner surface of the support and the outer surface of the ring.