โ๏ธ 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.
โก Fortran 90 Engine
Double Precision (IEEE 754)
โ ISO / ASME Validated
Convection
๐ Solver Telemetry
โ ACTIVE
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44
โก Solves
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๐ฆ Fortran Code
10.8 KB
๐
Released
Jun 2026
โฑ๏ธ Latency
< 1 ms
โ๏ธ Turbine Airfoil Blade Wall & Protective Coolant Film Layer
Real-time visual simulation: Angled cooling hole injection discharging protective thermal barrier film๐ Configuration & Presets
๐ฅ HPT First-Stage Vane
๐ Rotor Blade Showerhead
๐ญ Combustor Effusion Tile
๐ Scramjet Hypersonic Film
Goldstein & Baldauf Formulation:
โข Blowing Ratio: M = (ฯc Uc) / (ฯโ Uโ)
โข Momentum Flux Ratio: I = (ฯc Ucยฒ) / (ฯโ Uโยฒ)
โข Film Effectiveness: ฮท = (Taw โ Tโ) / (Tc โ Tโ)
โข Wall Heat Flux: qโณ = hโ ยท (Taw โ Tw) [kW/mยฒ]
โข Blowing Ratio: M = (ฯc Uc) / (ฯโ Uโ)
โข Momentum Flux Ratio: I = (ฯc Ucยฒ) / (ฯโ Uโยฒ)
โข Film Effectiveness: ฮท = (Taw โ Tโ) / (Tc โ Tโ)
โข Wall Heat Flux: qโณ = hโ ยท (Taw โ Tw) [kW/mยฒ]
๐ Film Cooling Results
Configure inputs and click Compute to view results.
๐ 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:
ฮท = (Taw โ Tโ) / (Tc โ Tโ) = 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.