恢復熱處理對蠕變損傷DZ125合金退化組織與性能的影響
發布人：上海艾荔艾合金股份有限公司www.shailiai.cn
更新時間：2016-03-11
以渦輪葉片用 DZ125 合金為研究對象, 通過蠕變中斷實驗模擬渦輪葉片的服役損傷, 并分別在 1230, 1240 和 1250 ℃進行恢復熱處理, 隨后再次進行與恢復熱處理前相同條件下的蠕變中斷實驗, 對比研究了恢復熱處理對 DZ125 合金蠕變退化組織與性能的影響.
恢復熱處理對蠕變損傷DZ125合金退化組織與性能的影響STUDY ON REJUVENATION HEAT TREATMENT OF A?DIRECTIONALLY-SOLIDIFIED SUPERALLOY DZ125 DAMAGED BY?CREEP?以渦輪葉片用 DZ125 合金為研究對象, 通過蠕變中斷實驗模擬渦輪葉片的服役損傷, 并分別在 1230, 1240 和 1250 ℃進行恢復熱處理, 隨后再次進行與恢復熱處理前相同條件下的蠕變中斷實驗, 對比研究了恢復熱處理對 DZ125 合金蠕變退化組織與性能的影響. 結果表明,?DZ125 合金在 980 ℃, 207 MPa 條件下經蠕變中斷實驗與恢復熱處理后, 引發再結晶的臨界應變量介于 3.5%~10%之間. 1230 ℃固溶熱處理部分消除了合金在1%蠕變過程中形成的粗大 γ’相, 導致其經 2 次時效處理后的基體組織中 γ’相大小不均勻, 從而部分恢復其原有性能. 固溶溫度進一步提高至 1240~1250 ℃, 不僅消除粗大 γ’相而且顯著降低殘余共晶 γ’含量, 并在時效處理后獲得均勻組織. 因此, 恢復熱處理的效果得到顯著提高, 達到甚至超過原有性能.?
The degradation of microstructure and property in turbine blades of aircraft engines is inevitable?during their service. Usually, rejuvenation heat treatment is applied to regenerate the original microstructure for?extending the service life of blades and improve economic returns. To date, systematic investigations about?rejuvenation heat treatment of the directionally-solidified superalloys are limited. In this work, the effect of?rejuvenation heat treatment on the degraded microstructure and property of DZ125 superalloy damaged by creep?was investigated. The interrupted creep test was first conducted on DZ125 superalloy to simulate the damage of?turbine blades during their service. Three rejuvenation heat treatments with the solution temperature at 1230, 1240?and 1250 ℃ were applied to the interrupted creep specimen. Then, the rejuvenated specimens were retested, and?their microstructures as well as creep properties were compared with those of the initial interrupted creep tests.?The results showed that no recrystallization occurred after the interrupted creep tests at 1% and 3.5% strain?followed by rejuvenation heat treatment, and the critical strain for the formation of the recrystallization was?between 3.5%~10%. The solution treatment at 1230 ℃ partially dissolved the coarse γ’ phase caused by creep?deformation, caused a nonuniform microstructure of γ/γ’ matrix after aging treatments, and resulting in partially?recovering the baseline creep property. However, the solution treatment at 1240 and 1250 ℃ could not only?dissolve the coarse γ’ phase but also reduce the fraction of residual γ’ eutectic significantly, and then regain a?uniform microstructure of γ/γ’ matrix after aging treatments. Hence, the effect of rejuvenation was further?improved, maintaining or exceeding the baseline creep property. This work will be helpful for understanding the?rejuvenation of turbine blades made of DZ125 superalloy and other directionally-solidified superalloys.?
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