Heat treatment of an alloy based on titanium aluminide
AssigneeSafran Aircraft Engines
InventorsGuillaume Martin, Céline Jeanne Marcillaud, Marie Mineur-Panigeon
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Abstract
The invention relates to a method for the treatment of an alloy based on titanium aluminide. The method comprises the following steps, during which no hot isostatic pressing is carried out: obtaining a semi-finished product (7) produced by centrifugal casting, then heat treating the semi-finished product in order to obtain an alloy microstructure comprising gamma grains and/or lamella grains (alpha2/gamma).
Claims16
A method for treating a titanium-aluminide alloy including 40 to 50 percent atomic (at %) aluminium, the method comprising the following steps:
- carrying out a centrifugal casting in a permanent mould in order to obtain a semi-finished product, and then
- heat treating the semi-finished product at a pressure below 1700×105 pascals (Pa) until a microstructure of the alloy comprising gamma grains and/or lamellar grains (alpha2/gamma) is obtained, wherein the heat treating is made between 1045° C. and 1255° C. during 10 to 40 hours.
A method for fabricating, without a hot isostatic pressing, a turbine-engine part made from titanium-aluminide alloy including 40 to 50 percent atomic (at %) aluminium, comprising the following steps:
- carrying out centrifugal casting in a permanent mould in order to obtain a semi-finished product with a form less complex than that of the finished product,
- heat treating the semi-finished product without hot isostatic pressing, at a pressure lower than 1700×105 pascals (Pa) until an alloy microstructure comprising gamma grains and/or lamellar grains (alpha2/gamma) is obtained, wherein the heat treating is made between 1045° C. and 1255° C. during 10 to 40 hours, and then
- machining the heat-treated semi-finished product to the form of said part.
Dependencies are inferred from the claim text.