Gradient Speed Control Method to Reduce the Residual Stress on a Turbine Disk in Forging Process

  • Yanju Wang
  • Jiaying Jiang
  • Yong Zhang
  • Yongjun Guan
  • Xingwu Li
Conference paper
Part of the Lecture Notes in Mechanical Engineering book series (LNME)

Abstract

The distribution of the residual stress on the turbine disk is affected by the forging process. The residual stress will reduce fatigue life of the turbine disk and increase the assemble error to meet the production. And the process parameters such as forging speed, forging temperature and friction will all affect the residual stress. In order to reduce the residual stress and improve the service life of the turbine disk, the relationship between the forging speed and residual stress on the turbine disk in the forging process was studied in this paper. By the combination of numerical simulation method and the forging process test, the numerical model of the forging process for the superalloy turbine disk was established, and the relationship between the residual stress distribution and forging speed was analyzed and calculated. Based on this, a gradient speed control method for reducing residual stress of the turbine disk was proposed. The calculation results showed that the gradient speed controlling in the forging process of the turbine disk effectively reduced the residual stress, decreased the usage and fee of the energy, and improved the service life of the turbine disk. According to the geometrical characteristics of the turbine disk, the gradient forging speed range was designed and optimized in this research. The results show that the residual stress of the turbine disk can be greatly reduced by the optimized gradient speed control method, which is a feasible way to reduce the residual stress of the superalloy turbine disks in the forging process.

Keywords

Gradient speed control Turbine disk Residual stress Forging process Deformation 

References

  1. 1.
    H. Feng, Study on the Durability of Critical Parts of Aviation Turbine Engine (Harbin Engineering University, 2015)Google Scholar
  2. 2.
    R.C. Benn, J.M. Davidson, K.R. Andryszak, Turbine blade superalloy I (1987)Google Scholar
  3. 3.
    S. Farahany, M. Aghaie-Khafri, A. Ourdjini et al., Influence of heat treatment on properties of hot isostatically pressed turbine blade superalloy IN738. Adv. Mater. Res. 264–265, 502–507 (2011)CrossRefGoogle Scholar
  4. 4.
    H.Y. Zhang, S.H. Zhang, Z.X. Li et al., Hot die forging process optimization of superalloy IN718 turbine disc using processing map and finite element method. Proc. Inst. Mech. Eng. Part B J. Eng. Manuf. 224(1), 103–110 (2010)CrossRefGoogle Scholar
  5. 5.
    N. Nayan, N.P. Gurao, S.V.S.N. Murty et al., Microstructure and micro-texture evolution during large strain deformation of Inconel alloy IN718. Mater. Charact. 110, 236–241 (2015)CrossRefGoogle Scholar
  6. 6.
    L.F. Zhao, L.I. Xing-Dong, L.I. Hui et al., Measurement of residual stress of nickel-base directionally crystallized superalloy blade in gas turbines. Therm. Turbine (2016)Google Scholar
  7. 7.
    M.N. James, D.G. Hattingh, D. Asquith et al., Applications of residual stress in combatting fatigue and fracture. Procedia Struct. Integrity 2, 11–25 (2016)CrossRefGoogle Scholar
  8. 8.
    A.G. Youtsos, Residual Stress and its Effects on Fatigue and Fracture (Springer, Netherlands, 2006)CrossRefGoogle Scholar
  9. 9.
    Y. Liu, Y. Ning, X. Yang et al., Effect of temperature and strain rate on the workability of FGH4096 superalloy in hot deformation. Mater. Des. 95, 669–676 (2016)CrossRefGoogle Scholar
  10. 10.
    Y. Liu, Z. Yin, J. Luo et al., The constitutive relationship and processing map of hot deformation in A100 steel. High Temp. Mater. Process. (London) 35(4), 399–405 (2016)Google Scholar

Copyright information

© Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  • Yanju Wang
    • 1
  • Jiaying Jiang
    • 2
  • Yong Zhang
    • 1
  • Yongjun Guan
    • 1
  • Xingwu Li
    • 1
  1. 1.Aviation Engine Corporation of ChinaBeijing Instititute of Aeronautical MaterialsBeijingChina
  2. 2.Department of Mechanical EngineeringImperical College LondonLondonUK

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