Powder Superalloy Short Crack Growth Model Considering Effects of Stress Ratio and Temperature

被引：0
|
作者：
Xu Y.-F. [1 ]
Hu D.-Y. [1 ,2 ,3 ]
Mao J.-X. [1 ,2 ,3 ,4 ]
Liu X.-L. [5 ]
Sun H.-H. [1 ,4 ]
Wang R.-Q. [1 ,2 ,3 ,6 ]
机构：
[1] Research Institute of Aero-Engine, Beihang University, Beijing
[2] Beijing Key Laboratory of Aero-Engine Structure and Strength, Beihang University, Beijing
[3] United Research Center of Mid-Small Aero-Engine, Beijing
[4] AECC Sichuan Gas Turbine Establishment, Chengdu
[5] AECC Beijing Institute of Aeronautical Materials, Beijing
[6] School of Energy and Power Engineering, Beihang University, Beijing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2023年 / 44卷 / 05期
关键词：
Engineering applicability; Life prediction; Powder superalloy; Short crack growth; Tanaka model;
D O I：
10.13675/j.cnki.tjjs.2207063
中图分类号：
学科分类号：
摘要：
Short crack growth has become the key to the fatigue life prediction of advanced powder turbine disks. In order to accurately simulate the short crack growth stage of powder superalloy materials，the effects of stress ratio and temperature on short crack growth of FGH96 powder superalloy were focused in this paper，and a method of short crack growth life prediction based on Tanaka model modification was established，which was engineering suitable. The crack closure parameters were used to characterize the effect of stress ratio and the thermodynamic theory was used to characterize the effect of temperature. The unified description of short crack growth law under different stress ratios and temperatures is achieved. Compared with the traditional model，it has significant advantages in prediction accuracy and engineering applicability，and the relative error with test results is less than 20%. © 2023 Journal of Propulsion Technology. All rights reserved.
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共 27 条
  • [1] (2006)
  • [2] (2014)
  • [3] 22, pp. 34-38, (2015)
  • [4] 61, 15, pp. 28-36, (2018)
  • [5] SONG Ying-dong, GAO De-ping, Turbine Engine Composite Route Flight Loading Spectrum Derivation［J］, Journal of Propulsion Technology, 21, 4, pp. 54-56, (2000)
  • [6] Pearson S., Fatigue Crack Propagation in Metals［J］, Nature, 211, 5053, pp. 1077-1078, (1966)
  • [7] Aratani M，, Knott J F., The Growth of Short Fatigue Cracks ahead of a Notch in High Strength Steel ［J］, Engineering Failure Analysis, 17, 1, pp. 200-207, (2010)
  • [8] Liao M., Dislocation Theory Based Short Crack Model and Its Application for Aircraft Aluminum Alloys［J］, Engineering Fracture Mechanics, 77, 1, pp. 22-36, (2010)
  • [9] Wang Z, Qian G，, Et al., In-Situ SEM Investigation on Fatigue Behaviors of Additive Manufactured Al-Si10-Mg Alloy at Elevated Temperature［J］, Engineering Fracture Mechanics, 214, pp. 149-163, (2019)
  • [10] Li S，, Et al., In Situ Observation for the Fatigue Crack Growth Mechanism of 316L Stainless Steel Fabricated by Laser Engineered Net Shaping［J］, International Journal of Fatigue, 130, (2020)
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