✈️ Turbine Blade Film Cooling Effectiveness
Evaluate gas turbine film cooling effectiveness (eta), adiabatic wall temperature (Taw), blowing ratio (M), momentum flux ratio (I), and protected wall heat flux reduction.
⚡ Fortran 90 Engine
Double Precision (IEEE 754)
✓ ISO / ASME Validated
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Jun 2026
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✈️ Turbine Airfoil Blade Wall & Protective Coolant Film Layer
Real-time visual simulation: Angled cooling hole injection discharging protective thermal barrier film📝 Configuration & Presets
🔥 HPT First-Stage Vane
🌀 Rotor Blade Showerhead
🏭 Combustor Effusion Tile
🚀 Scramjet Hypersonic Film
Goldstein & Baldauf Formulation:
• Blowing Ratio: M = (ρc Uc) / (ρ∞ U∞)
• Momentum Flux Ratio: I = (ρc Uc²) / (ρ∞ U∞²)
• Film Effectiveness: η = (Taw − T∞) / (Tc − T∞)
• Wall Heat Flux: q″ = h₀ · (Taw − Tw) [kW/m²]
• Blowing Ratio: M = (ρc Uc) / (ρ∞ U∞)
• Momentum Flux Ratio: I = (ρc Uc²) / (ρ∞ U∞²)
• Film Effectiveness: η = (Taw − T∞) / (Tc − T∞)
• Wall Heat Flux: q″ = h₀ · (Taw − Tw) [kW/m²]
📊 Film Cooling Results
Configure inputs and click Compute to view results.
📘 Calculation Methodology & Film Cooling Standards
Goldstein & Baldauf Correlations
Computes the adiabatic wall temperature $T_{aw}$ resulting from the thermal mixing between the injected cold wall jet and mainstream boundary layer:
η = (Taw − T∞) / (Tc − T∞) = f(x/(MD), I, P/D)
Jet Attachment vs Lift-Off
When momentum flux ratio $I > 0.8$, the coolant jet lifts off the surface, entraining hot gas beneath before reattaching, degrading near-hole protection.
Key Engineering Assumptions
- Rows of discrete circular holes inclined at $\alpha \approx 30^\circ - 35^\circ$.
- Turbulent boundary layer mixing over flat or mildly curved airfoil walls.
- Applicable to gas turbine vanes, blades, combustors, and scramjet injectors.