| name | laser-peening |
| description | Laser peening (laser shock peening, LSP) — plasma pressure pulse, Hugoniot elastic limit, compressive residual stress depth, comparison to shot peening, process parameters (fluence, spot size, overlay, water confinement), fatigue life improvement, FOD tolerance, aerospace AMS 2546, Ti-6Al-4V/Ni alloy applications. |
| metadata | {"priority":7,"promptSignals":{"phrases":["laser peening","laser shock peening","LSP","laser peen","shock peening","laser induced residual stress"],"minScore":3}} |
Laser Shock Peening (LSP) — Complete Skill
Physical Mechanism
Laser-Plasma Pressure Generation
LSP process sequence:
- High-power short laser pulse (ns duration) strikes opaque ablative coating on metal surface
- Ablation creates rapidly expanding plasma (T > 10,000 K; P > 1 GPa)
- Water confinement layer (1–3 mm) constrains plasma → amplifies peak pressure 3–5×
- Shock wave propagates into metal at ~5 km/s
- Shock pressure > Hugoniot Elastic Limit (HEL) → plastic deformation in thin layer → compressive residual stress upon relaxation
Shock wave pressure (laser):
P_shock = √(2α_eff × I / (A_acoustic × Z)) [approximate; α_eff = fraction of energy in shock wave ≈ 0.2; I = laser intensity [W/cm²]; Z = acoustic impedance; A_acoustic = acoustic impedance coefficient]
Simplified pressure formula (Fabbro model):
P [GPa] = 0.01 × √(α_eff × Z_eff × I [W/cm²])
Z_eff = 2 Z₁Z₂/(Z₁+Z₂) [Z₁ = water impedance = 1.65×10⁵ g/(cm²·s); Z₂ = metal impedance; Ti-6Al-4V: Z₂ = 2.8×10⁶]
Typical P_shock = 2–6 GPa for I = 10⁸–10¹⁰ W/cm²
Hugoniot Elastic Limit (HEL):
HEL = dynamic yield stress under uniaxial strain (shock loading)
HEL = σ_y × (1-ν) / (1-2ν) × (1/(1+ν)) × √(3) [approximate from quasi-static σ_y and Poisson ν]
For Ti-6Al-4V: HEL ≈ 2.8 GPa (σ_y_dyn ≈ 1.5 GPa); for 300M steel: HEL ≈ 5.5 GPa
Plastic deformation condition: P_shock > HEL → plastic strain → residual compression
Residual Stress Profile
Depth of compressive layer:
z_comp ≈ 2C_L × τ_p / 3 [approximate; C_L = longitudinal wave velocity; τ_p = shock pulse duration]
For Ti-6Al-4V: C_L = 6,300 m/s; τ_p = 25 ns → z_comp ≈ 2 × 6,300 × 25×10⁻⁹ / 3 = 0.11 mm
Actual with multiple overlapping pulses: z_comp = 1–4 mm (much deeper than shot peening)
Residual stress magnitude:
Surface: σ_residual = -0.5 to -1.0 × σ_y (compressive)
At depth z_comp: stress transitions from compressive to slight tension (equilibrium)
For Ti-6Al-4V: surface σ_residual ≈ -700 to -1,200 MPa; z_comp = 1.5–2.5 mm
Comparison to shot peening:
Shot peening: depth < 0.3 mm; surface σ_residual = -400 to -700 MPa
Laser peening: depth 1–4 mm; σ_residual = -700 to -1,400 MPa
LSP advantage: 5–10× deeper → protects against fatigue cracks that initiate at depth
Process Parameters
Laser Parameters
Pulse energy: 5–50 J per pulse
Pulse duration: 10–30 ns (Nd:YAG Q-switched; 1.064 μm wavelength)
Spot size: 2–10 mm diameter (flat-top beam profile preferred)
Fluence (energy per area):
F = E_pulse / A_spot [J/cm²; target F = 5–25 J/cm²]
F < 5 J/cm²: insufficient pressure for HEL excitation
F > 25 J/cm²: ablation without confinement benefits; surface damage possible
Laser intensity:
I = F / τ_p [W/cm²; I = 10⁸–10¹⁰ W/cm²]
Repetition rate: 1–20 Hz (limited by laser thermal management and water flow refresh rate)
Confinement Layer
Water jet or water sheet: 1–3 mm thick flowing water
Flow rate: 5–15 L/min; uniform coverage; no bubbles (bubbles → plasma breakthrough → lost confinement)
Transparent to Nd:YAG 1.064 μm → laser passes through water without loss
Function: plasma confinement → shock pressure amplified 3–5× vs. open-air ablation
Ablative coating (sacrificial):
Black paint (3M 1522-2): most common; 100–150 μm thick; applied by robot
Aluminum foil (50–100 μm): self-adhesive; consistent ablation properties; easier on complex curves
Purpose: absorb laser energy → plasma; protects metal surface from direct ablation
Without coating: laser melts metal surface directly → thermal damage, undesirable microstructure
Coverage (overlap pattern):
Spot coverage: 100% of surface treated at least once; often 2× coverage (100% overlap)
Pattern: square grid or hexagonal; spacing = (1 - overlap_fraction) × spot_diameter
2× coverage (100% overlap): stronger compressive layer; used for critical aerospace parts
Materials and Applications
Ti-6Al-4V (Titanium)
Primary aerospace application: fan blades, disk bores, blade dovetails
Baseline properties: σ_y = 910 MPa; σ_UTS = 1,000 MPa; ρ = 4,430 kg/m³
LSP effect:
Pre-LSP fatigue life at 800 MPa alternating stress: ~10⁵ cycles
Post-LSP fatigue life at 800 MPa: > 10⁷ cycles (> 100× improvement)
Fretting fatigue (blade-disk dovetail): LSP increases fretting fatigue strength 50–100%
FOD (Foreign Object Damage) tolerance:
Ti-6Al-4V fatigue limit without LSP: drops from 600 MPa to 250 MPa after FOD notch (simulated bird strike nick, 0.5 mm depth)
After LSP: FOD fatigue limit maintained at 500 MPa (compressive stress closes notch tip)
Nickel Superalloys (Inconel 718, René 95)
Application: turbine disk bores, blade roots, firtree slots
Challenge: very high HEL (> 4 GPa) → requires highest laser intensity (I > 10⁹ W/cm²)
Result: σ_residual = -900 to -1,400 MPa; depth = 1–3 mm
Benefit: bore stress from centrifugal loading partially offset by compressive residual → increased disk life or weight reduction
Steel (300M, 4340, 17-4 PH)
Landing gear and structural components:
300M: σ_y = 1,650 MPa; LSP surface stress = -1,200 MPa → net improved fatigue at stress concentrations
Landing gear cylinders: LSP on inner bore → delays fatigue crack initiation from hoop stress
Shot peening often replaced by LSP for critical structural steel (deeper protection)
Aluminum (7075, 2024)
Lower HEL (~0.5–0.7 GPa) → LSP achieves good depth at lower laser intensity:
z_comp = 2–4 mm (deepest compared to titanium/steel)
σ_residual = -200 to -350 MPa (lower absolute but proportionally significant vs. σ_y ≈ 500 MPa for 7075)
Applications: aircraft lap joints, fastener holes, rivet holes (pitting corrosion fatigue)
Quality Assurance
X-ray diffraction (XRD): gold standard for residual stress measurement
Bragg's law: 2d sinθ = nλ; strain = (d - d₀)/d₀; stress from generalized Hooke's law
Depth profile: electrochemical layer removal (electrolytic etching) + XRD at each depth; destructive but precise
Hole drilling method (ASTM E837): semi-destructive; 0.5–1.2 mm end mill removes material; strain gauge rosette measures strain relief → back-calculate stress
Resolution: 0.3–1.5 mm depth; good for moderate depth; faster than XRD profiling
Neutron diffraction: large facility (reactor/spallation); bulk measurement; 10–20 mm depth; non-destructive for thin parts
Confirmation by fatigue testing:
Replicate coupons: with and without LSP; run-out comparison at S-N specific stress level
ASTM E466 (axial S-N); ASTM E2709 (statistical design of fatigue testing)
Cost and Process Economics
Processing rate: 10–50 cm²/min (limited by pulse rate and overlap)
Cost comparison:
Shot peening: $5–20/kg; fast; cheap
Laser peening: $50–500/kg; slow; expensive equipment ($2–5M capital)
Justified for: critical fatigue-limited parts (fan blades, landing gear) where longer life or weight reduction offsets cost
Fatigue life multiplier:
Ti-6Al-4V blade: 10–100× life with LSP → extended maintenance interval → total cost competitive
Landing gear: replace shot peening with LSP → reduce wall thickness 5–15% → weight savings on large aircraft
Standards
| Standard | Scope |
|---|
| AMS 2546 | Laser shock peening of metallic components |
| AMS 2430 | Shot peening (for comparison) |
| ASTM E837 | Hole drilling residual stress measurement |
| SAE ARP 4761 | Guidelines for safety assessment (LSP process qualification) |
| MIL-S-13165 | Shot peening (military, for comparison) |
| ASTM E466 | Axial fatigue testing (coupon qualification) |
Output
Provide: material (alloy, σ_y [MPa], HEL [GPa]), part type and critical feature (blade, bore, dovetail), laser parameters (pulse energy [J], duration [ns], spot size [mm], fluence [J/cm²]), confinement layer (water thickness [mm], flow rate [L/min]), ablative coating type and thickness [μm], coverage pattern (overlap %, number of passes), predicted surface residual stress σ_residual [MPa] (compressive), depth of compression z_comp [mm], comparison to shot peening (depth, stress magnitude), fatigue life improvement factor (from test data or prediction), FOD tolerance improvement [%], residual stress measurement method (XRD/neutron/hole-drill), applicable standard (AMS 2546, ASTM E837, ASTM E466).
