๐ฅ Gas Turbine Combustor (Lefebvre Model)
Size gas turbine combustor chambers: Lefebvre combustion volume and loading parameter, fuel flow, primary flame temperature, pattern factor OTDF, and liner geometry.
โก Fortran 90 Engine
Double Precision (IEEE 754)
โ ISO / ASME Validated
Turbomachinery
๐ Solver Telemetry
โ ACTIVE
๐๏ธ Views
40
โก Solves
32
๐พ Downloads
306
๐ฆ Fortran Code
5.2 KB
๐
Released
Jun 2026
โฑ๏ธ Latency
< 1 ms
๐ฅ Combustor Liner, Swirler Flame & Dilution Jets
Real-time visual simulation: Fuel swirler primary flame, secondary mixing, and dilution air jets๐ Configuration & Presets
๐ญ Frame 7/9 Heavy Duty
โ๏ธ Aero Turbofan Jet-A
๐ฟ 100% Hydrogen Can-Annular
โก Microturbine Single Can
Lefebvre Combustor Formulation:
โข Fuel Flow: แนf = แนa ยท [cpgยทT4 โ cpaยทT3] / [ฮทcยทLHV โ cpgยทT4] [kg/s]
โข Lefebvre Loading: ฮธ = [P31.75 ยท Vcomb ยท exp(T3/300)] / แนa
โข Thermal Duty: Qฬth = แนf ยท LHV [MWth]
โข Pattern Factor (OTDF): (Tmax โ T4) / (T4 โ T3) < 0.25.
โข Fuel Flow: แนf = แนa ยท [cpgยทT4 โ cpaยทT3] / [ฮทcยทLHV โ cpgยทT4] [kg/s]
โข Lefebvre Loading: ฮธ = [P31.75 ยท Vcomb ยท exp(T3/300)] / แนa
โข Thermal Duty: Qฬth = แนf ยท LHV [MWth]
โข Pattern Factor (OTDF): (Tmax โ T4) / (T4 โ T3) < 0.25.
๐ Performance Results
Configure inputs and click Compute to view results.
๐ Calculation Methodology & Combustor Standards
Lefebvre 3-Zone Combustor Architecture
Combustion air is metered into a primary reaction zone (25โ30%) for flame stabilization, intermediate zone (20โ25%) for CO burnout, and dilution zone (45โ55%) to shape the radial temperature profile for the downstream turbine.
Pattern Factor & Liner Sizing
Overall Temperature Distribution Factor (OTDF) measures peak circumferential temperature hotspots, preventing turbine nozzle guide vane melting.
Key Engineering Assumptions
- Lefebvre semi-empirical combustion loading formulation.
- Annular and can-annular configurations.
- Widely used in aero-engines, power generation gas turbines, and hydrogen combustors.