🔥 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.

⚡ Fortran 90 Engine Double Precision (IEEE 754) ✓ ISO / ASME Validated

Turbomachinery

📊 Solver Telemetry ● ACTIVE

👁️ Views 40

⚡ Solves 32

💾 Downloads 308 📦 Fortran Code 5.2 KB

📅 Released Jun 2026

⏱️ Latency < 1 ms

🔥 Combustor Liner, Swirler Flame & Dilution Jets

Real-time visual simulation: Fuel swirler primary flame, secondary mixing, and dilution air jets

📝 Configuration & Presets

🏭 Frame 7/9 Heavy Duty ✈️ Aero Turbofan Jet-A 🌿 100% Hydrogen Can-Annular ⚡ Microturbine Single Can

🧪 Fuel Medium & Airflow

Fuel Type:

Airflow ṁ_air [kg/s]:

Inlet Pressure P₃ [bar a]:

🌡️ Temperatures & Architecture

Inlet Temp T₃ [K]:

Turbine Inlet TIT T₄ [K]:

Number of Cans (1=Annular):

Pressure Drop ΔP/P₃ [%]:

Lefebvre Combustor Formulation:
• Fuel Flow: ṁ_f = ṁ_a · [c_pg·T₄ − c_pa·T₃] / [η_c·LHV − c_pg·T₄] [kg/s]
• Lefebvre Loading: θ = [P₃^1.75 · V_comb · exp(T₃/300)] / ṁ_a
• Thermal Duty: Q̇_th = ṁ_f · LHV [MWth]
• Pattern Factor (OTDF): (T_max − T₄) / (T₄ − T₃) < 0.25.

📊 Performance Results

📊 Output Summary
💾 Fortran Source

Combustor Thermal Heat Release (Q̇_th)

54.3 MWth

Fuel: 1.26 kg/s | Efficiency: 95.00%

HIGH THERMAL NOX ZONE

Primary Flame Temperature 2450 K 2177 °C

Combustor Volume (V_comb) 0.141 m³ Residence time ~ 6 ms

Liner Diameter × Length 422 × 1012 mm Annular Liner

Overall Pattern Factor (OTDF) 0.20 Turbine nozzle thermal safety

📈 Combustor Volume (m³) vs Inlet Pressure P3 (bar)

📊 Fuel Flow (kg/s) vs Turbine Inlet Temp T4 (K)

=================================================================
 THERMOFLUIDCALC — GAS TURBINE COMBUSTOR REPORT
=================================================================
Case Title                 : Aviation Turbofan High-Pressure Annular Combustor
Fuel Medium                : Aviation Kerosene Jet-A (LHV = 43.1 MJ/kg, FARstoich = 0.068)
Operating State            : mair = 45.00 kg/s, P3 = 30.0 bar, T3 = 820.0 K, T4 = 1750.0 K
Combustor Architecture     : Annular, L/D = 2.4, dp = 4.5%
-----------------------------------------------------------------
THERMAL HEAT RELEASE (Q_th): 54.25 MWth
Fuel Mass Flow Rate (m_f)  : 1.259 kg/s (FAR = 0.0280, phi = 0.41)
Primary Flame Temperature  : 2450.0 K (2176.8 C)
Combustor Volume (V_comb)  : 0.1412 m3
Liner Dimensions           : D = 421.5 mm, L = 1011.7 mm
Combustion Efficiency      : 95.00%
Overall Pattern Factor OTDF: 0.200 (HIGH THERMAL NOX ZONE)
=================================================================

📘 Calculation Methodology & Combustor Standards

Lefebvre 3-Zone Combustor Architecture

Combustion air is metered into a primary reaction zone (25–30%) for flame stabilization, intermediate zone (20–25%) for CO burnout, and dilution zone (45–55%) 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.

ThermoFluidCalc Engineering Report