US2024384383A1PendingUtilityA1

Process for manufacturing a nickel-based alloy product

Assignee: SAFRAN AIRCRAFT ENGINESPriority: Jul 15, 2021Filed: Jul 8, 2022Published: Nov 21, 2024
Est. expiryJul 15, 2041(~15 yrs left)· nominal 20-yr term from priority
C22C 19/03C22B 9/20C22B 9/18C22F 1/10
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Claims

Abstract

Method for manufacturing a nickel-based alloy product, including: a step of supplying an ingot of a nickel-based alloy including at least one intermetallic phase, a first forging step of forging the ingot, during which the true strain rate is less than 1 s −1 , a second forging step of forging the ingot, during which the true strain rate is greater than 1 s −1 , and a step of static recrystallisation, after the second forging step, during which the ingot is exposed to a temperature of between 1000 and 1055° C. for a duration of between 30 minutes and 10 hours.

Claims

exact text as granted — not AI-modified
1 . A method for manufacturing a nickel-based alloy product, comprising:
 a step of supplying an ingot of a nickel-based alloy comprising at least one γ′ intermetallic phase combining nickel with aluminium and/or titanium, said at least one γ′ intermetallic phase being present in the alloy of the ingot at a level of 30% to 50% by weight,   a first forging step of forging the ingot, during which the true strain rate is less than 1 s −1 , the first forging step being carried out at a temperature between 1050 and 1150° C.,   a second forging step of forging the ingot, during which the true strain rate is greater than 1 s −1 , and   a step of static recrystallisation, after the second forging step, during which the ingot is exposed to a temperature of between 1000 and 1055° C. for a duration of between 30 minutes and 10 hours.   
     
     
         2 . The method according to  claim 1 , wherein said at least one γ′ intermetallic phase is present in the alloy of the ingot at a level of 35% to 45% by weight. 
     
     
         3 . The method according to  claim 1 , wherein, before the supplying step, the ingot has undergone a vacuum remelting step. 
     
     
         4 . The method according to  claim 1 , wherein the first forging step leads to a strain of the ingot greater than 1. 
     
     
         5 . The method according to  claim 1 , wherein the second forging step is carried out at a temperature between 900 and 1055° C. 
     
     
         6 . The method according to  claim 1 , wherein the second forging step leads to a strain of the ingot greater than 0.2. 
     
     
         7 . The method according to  claim 1 , wherein the recrystallisation step is carried out at a temperature between 1000° C. and 1025° C. and for a duration between 1 hour and 10 hours. 
     
     
         8 . The method according to  claim 1 , wherein the recrystallisation step is carried out at a temperature between 1025° C. and 1055° C. and for a duration between 30 minutes and 2 hours. 
     
     
         9 . The method according to  claim 1 , wherein the second forging step leads to a strain of the ingot greater than 0.5. 
     
     
         10 . The method according to  claim 1 , wherein the recrystallisation step is carried out at a temperature between 1000° C. and 1010° C. and for a duration between 4 hours and 6 hours. 
     
     
         11 . The method according to  claim 1 , wherein the recrystallisation step is carried out at a temperature between 1045° C. and 1055° C. and for a duration between 50 minutes and 70 minutes.

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