The effect of warm laser shock peening on the thermal stability of compressive residual stress and the hot corrosion resistance of Ni-based single-crystal superalloy

Tang, Zhanghan; Dong, Xia; Geng, Yan; Wang, Kedian; Duan, Wenqiang; Gao, Meng; Mei, Xuesong

doi:10.1016/j.optlastec.2021.107556

Cited by 26 publications

(9 citation statements)

References 41 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Additionally, the presence of slip bands was noted by several authors [5,45,58] in this region and was attributed to the formation of dislocation tangles which were able to overcome the critical shearing stress of the γ' phases, and consequently initiate the slipping mechanism. limited in [45,53] and it is possible that with much longer exposure (comparable to the service life of a turbine blade), residual stresses may further decrease.…”

Section: Microstructure Modifications Resulting From Lpmentioning

confidence: 99%

“…While these techniques are used extensively for residual stress calculation of polycrystalline materials, they are rarely used for single crystalline materials due to additional experimental complexity associated with differences in diffraction behavior [45]. Because of this, an alternative XRD method is often utilized in which the peak shift corresponding to a specific diffraction plane is measured and subsequently converted into strain and stress values [45,52,53] The diffraction peaks for both the γ and γ' phases corresponding to a given (hkl) plane were collected and their Bragg angles were converted to d-spacings by Bragg's law, nλ = 2d (hkl) sin θ (7) where λ is X-ray wavelength, d (hkl) is the interplanar spacing of the (200) plane, θ is Bragg Angle corresponding to the given (hkl) peak, and n is the diffraction order. After separation, the peak centered around a higher Bragg Angle corresponds to the γ' phase while the peak centered around a lower Bragg angle corresponds to the γ phase.…”

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

“…Although some degree of residual stress relaxation is expected, it is evident that enhancing dislocation pinning effects within the LP-affected microstructure is required to increase the thermal stability of plastic deformation and consequently, residual stresses. Tang et al [53] treated DD6 with WLSP and measured the relaxation behavior following thermal exposure of 980 °C for 10 h (Figure 4e,f). Surface compressive residual stresses Although some degree of residual stress relaxation is expected, it is evident that enhancing dislocation pinning effects within the LP-affected microstructure is required to increase the thermal stability of plastic deformation and consequently, residual stresses.…”

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

“…Surface compressive residual stresses Although some degree of residual stress relaxation is expected, it is evident that enhancing dislocation pinning effects within the LP-affected microstructure is required to increase the thermal stability of plastic deformation and consequently, residual stresses. Tang et al [53] treated DD6 with WLSP and measured the relaxation behavior following thermal exposure of 980 • C for 10 h (Figure 4e,f). Surface compressive residual stresses relaxed by ~15-17% in the WLSP specimens and around 30% for the LP specimen.…”

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

“…The increased retention of stresses in the WLSP specimens is attributed to DSA effects which increased the energy barrier for dislocation movement. While the degree of relaxation is relatively mild in the WLSP specimens, (which certainly shows the promise of modified LP processes for use in turbine blade applications) the thermal exposure durations were limited in [45,53] and it is possible that with much longer exposure (comparable to the service life of a turbine blade), residual stresses may further decrease.…”

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

See 4 more Smart Citations

A Review of Laser Peening Methods for Single Crystal Ni-Based Superalloys

Holtham

Davami

2022

Metals

View full text Add to dashboard Cite

Single crystal Ni-based superalloys are often used to create gas turbine engine blades for their high strength under intense thermo-mechanical loading. Though they are remarkably capable under these conditions, a particular class of premature failure mechanisms known as surface-initiated damage mechanisms can lead to the early fracture of an otherwise healthy blade. This review paper discusses the current progress of post-processing techniques that can greatly mitigate the potency of surface-initiated damage mechanisms. In particular, laser peening (LP) is of significant interest due to the relatively low amount of cold work it induces, greater depth of compressive residual stresses than other cold working methods, ability to accommodate complex part geometries, and the minuscule effect it has on surface roughness. The residual stresses imparted by LP can greatly hinder crack growth and consequently allow for enhanced fatigue life. Given that turbine blades (constructed with single crystal Ni-based superalloys) are prone to fail by these mechanisms, LP could be a worthy choice for increasing their service lives. For this reason, initiative has been taken to better understand the mechanical and microstructural modifications imparted by LP on single crystal Ni-based superalloys and a summary of these investigations are presented in this review. Results from several works show that this class of alloy responds well to LP treatment with improvements such as ~30–50% increase in microhardness, 72% increase in low cycle fatigue life, and elevated resistance to hot corrosion. The primary objective of this review is to provide insight into current state-of-the-art LP techniques and summarize the findings of numerous works which have utilized LP for increasing the service lives of single crystal Ni-based superalloy components.

show abstract

Section: Microstructure Modifications Resulting From Lpmentioning

confidence: 99%

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

Section: Residual Stress Distribution and Measurement Following Lpmentioning

confidence: 99%

See 3 more Smart Citations

A Review of Laser Peening Methods for Single Crystal Ni-Based Superalloys

Holtham

Davami

2022

Metals

View full text Add to dashboard Cite

show abstract

A Critical Review of Laser Shock Peening of Aircraft Engine Components

Huang

Zou³

et al. 2023

Adv Eng Mater

View full text Add to dashboard Cite

Many aviation accidents are caused by the failure of aircraft engine components, and engine blades are especially vulnerable to high‐cycle fatigue fracture in severe working environments as well as to impact damage caused by foreign objects. To address this problem, the United States took the lead and has been successful in implementing laser shock peening (LSP) as a surface treatment for aircraft engine components to enhance their fatigue performance. This review provides an overview of the development of LSP for use in treating aircraft engine components over the past three decades, with a brief introduction to the development of high‐energy pulsed lasers for LSP. A particular focus of this review is on the limitations and challenges associated with the application of LSP for treating critical aircraft engine components. It is hoped that this review serves as a reference for future research and development that can lead to better performance of these components.

show abstract

Effects of high-energy laser peening followed by pre-hot corrosion on stress relaxation, microhardness, and fatigue life and strength of single-crystal nickel CMSX-4® superalloy

Morar

Holtham

Hackel

et al. 2023

Int J Adv Manuf Technol

View full text Add to dashboard Cite

This study investigated the stress relaxation and fatigue life and strength of laser-peened single-crystal nickel superalloy specimens compared to unpeened and shot-peened specimens following hot corrosion exposure and then fatigue testing. The specimens were treated by conventional laser peening and a new cyclic laser peening plus thermal microstructure engineering process. The latter treatment supports the benefit of a unique process involving application of layers of laser peening using high energy with large footprint spots combined with interspersed cyclic annealing. Stress measurements by slitting showed the plastic penetration depth of laser peening exceeded shot peening by a factor of 24. Unpeened and peened specimens were exposed to sulphate corrosives at 700 °C for 300 h and then fatigue tested. Tests of five non-laser-peened specimens all failed in low-cycle fatigue regime, whereas three identically tested laser-peened specimens all achieved multi-million-cycle runout without failure, indicating fully consistent large benefit for life by laser peening. Additional tests also showed fatigue strength improvement of 2:1 by laser peening. Residual stress measurements post hot-corrosion exposure and fatigue testing showed notable 5 mm depth retention of residual eigenstress in a laser-peened specimen.

show abstract

The effect of warm laser shock peening on the thermal stability of compressive residual stress and the hot corrosion resistance of Ni-based single-crystal superalloy

Cited by 26 publications

References 41 publications

A Review of Laser Peening Methods for Single Crystal Ni-Based Superalloys

A Review of Laser Peening Methods for Single Crystal Ni-Based Superalloys

A Critical Review of Laser Shock Peening of Aircraft Engine Components

Effects of high-energy laser peening followed by pre-hot corrosion on stress relaxation, microhardness, and fatigue life and strength of single-crystal nickel CMSX-4® superalloy

Contact Info

Product

Resources

About