Method for producing a metal part for an aircraft turbo-engine
View Patent ↗A method for producing a metal part, the part including, in particular, a first set of elements having a small thickness, and a second set of elements having a large thickness, the method including: forming a peripheral portion of the elements of the second set of elements by selectively melting a powder by scanning the surface of the powder layer with a laser beam or with an electron beam; using the peripheral portion of the elements of the second set of elements as a mould by carrying out an operation of filling an inner area defined by the peripheral portion with liquid metal; cooling the metal part to solidify the inner area defined by the peripheral portion and filled with metal.
1. Method for producing a metal part, said part comprising a first set of elements having a small thickness comprised between 0.3 millimeters and 4 millimeters, and a second set of elements having a large thickness greater than four millimeters, the metal part being a part of an aircraft turbo-engine, said method comprising:
forming a peripheral portion of the elements of the second set of elements by selectively melting a metal powder by scanning a surface of a powder layer with a laser beam or with an electron beam;
using the peripheral portion of the elements of the second set of elements as a mould by carrying out an operation of filling an inner area defined by said peripheral portion with liquid metal;
cooling the metal part to solidify the inner area, defined by the peripheral portion and filled with metal.
2. Method according to claim 1 , comprising forming the elements of the first set of elements by selectively melting a powder by scanning the surface of the powder layer with the laser beam or with the electron beam.
3. Method according to claim 2 , wherein forming the peripheral portion of the elements of the second set of elements and forming the elements of the first set of elements are carried out before the operation of filling the inner area defined by the peripheral portion of the elements of the second set of elements.
4. Method according to claim 1 , wherein the peripheral portion of the elements of the second set of elements formed by selectively melting powder defines an open volume.
5. Method according to claim 1 , wherein the peripheral portion of the elements of the second set of elements formed by selectively melting powder defines a closed volume having at least one orifice.
6. Method according to claim 1 , comprising, prior to the operation of filling the inner area defined by the peripheral portion of the elements of the second set of elements, removing the powder not used during the formation of the peripheral portion of the elements of the second set of elements.
7. Method according to claim 1 , wherein the elements of the second set of elements are platforms of a turbomachine compressor turbine for an aircraft and wherein the elements of the first set of elements are blades forming blend radii between said platforms.
8. Method for producing a metal part, said part comprising a first set of elements having a first thickness and a second set of elements having a second thickness that is larger than the first thickness, the metal part being a part of an aircraft turbo-engine, said method comprising:
forming a peripheral portion of the elements of the second set of elements by selectively melting a metal powder by scanning a surface of a powder layer with a laser beam or with an electron beam;
using the peripheral portion of the elements of the second set of elements as a mould by carrying out an operation of filling an inner area defined by said peripheral portion with liquid metal;
cooling the metal part to solidify the inner area, defined by the peripheral portion and filled with metal.
9. Method according to claim 8 , wherein the first thickness is between 0.3 millimeters and 4 millimeters and the second thickness is greater than four millimeters.