鎳基高溫合金疲勞-蠕變壽命預(yù)測(cè)的臨界面損傷方法

鎳基高溫合金疲勞-蠕變壽命預(yù)測(cè)的臨界面損傷方法Critical Plane Damage Method for Fatigue-creep Life Prediction of Nickel-based Superalloy

采用臨界面損傷方法并耦合疲勞-蠕變壽命模型，通過(guò)適當(dāng)?shù)募夹g(shù)改進(jìn)，分別對(duì)某型航空發(fā)動(dòng)機(jī)650℃條件下渦輪盤(pán)用材料ZSGH4169高溫合金和980℃條件下渦輪轉(zhuǎn)子葉片用材料DZ125定向凝固高溫合金的疲勞-蠕變壽命進(jìn)行預(yù)測(cè)，并分別比較以Walls，Ccb，Swt，Glk，和Fin為參數(shù)的五種壽命模型的預(yù)測(cè)精度。算例的計(jì)算結(jié)果表明：對(duì)于ZSGH4169高溫合金，以Walls臨界損傷平面為參數(shù)的壽命模型預(yù)測(cè)效果較好，預(yù)測(cè)的結(jié)果與實(shí)驗(yàn)值相比基本落在±3倍分散帶以?xún)?nèi)；而對(duì)于DZ125高溫合金而言，以Glk臨界損傷平面為參數(shù)的壽命模型預(yù)測(cè)效果較好，預(yù)測(cè)的結(jié)果與實(shí)驗(yàn)值相比基本落在±2.5倍分散帶以?xún)?nèi)。

Adopting the classical critical plane damage method coupling fatigue-creep life models with adequate technique modification, the life predications of ZSGH4169 superalloy at 650℃and DZ125 superalloy at 980℃ were investigated to compare the predication accuracies of the five kinds of fatigue-creep life models, i.e. based on Walls, Ccb, Swt, Glk and Fin. The results of typical examples show that the fatigue-creep model based on Walls is the best for ZSGH4169 superalloy at 650℃,and the predicted life falls within ±3 scatter band of the test data, while the fatigue-creep model based on Glk is the best for DZ125 superalloy at 980℃, and the predicted life falls within ±2.5 scatter band of the test data.

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