Gas Turbine & Brayton Cycle Workspace
A comprehensive gas turbine performance simulator based on the Brayton cycle. Analyze compressor and turbine work, net power output, thermal efficiency, and exhaust temperature with real-time visualization of the thermodynamic process.
Cycle Parameters
Compressor discharge pressure / inlet pressure
Temperature at turbine entry (combustor outlet)
Working fluid mass flow through the engine
Isentropic efficiency of the compressor
Isentropic efficiency of the turbine
Brayton Cycle Flow
Cycle Performance
ResolvedCompressor Work
19.89 kkW
Turbine Work
38.10 kkW
Net Power
18.20 kkW
Thermal Efficiency
44.3%
Exhaust Temp
736.3 K
Power Ratio
52.2%
Specific Work
364.04 kW·s/kg
Temperature Profile
ΔT_comp
395.9 K
ΔT_turb
663.7 K
TIT
1400.0 K
Thermal Efficiency
44.3%
Net Output
18.20 k kW
RPM Estimate
13416 RPM
Operating Points
Compressor Work Ratio
52.2%
of turbine work
Specific Fuel Consumption
0.63 g/kWh
Simplified estimate
T₂s (Ideal)
624.7 K
T₂ (Actual)
684.0 K
T₄s (Ideal)
645.8 K
T₄ (Actual)
736.3 K
Thermal Assessment
01 / Brayton Cycle
Ideal & Real Cycle Analysis
The Brayton cycle is the thermodynamic model for gas turbine engines. It consists of isentropic compression, constant-pressure heat addition, isentropic expansion, and constant-pressure heat rejection.
Engineering note
Real gas turbine cycles include component inefficiencies (ηc, ηt) which reduce the net work output compared to the ideal Brayton cycle. The compressor consumes a significant portion (40-70%) of the turbine's power output.
02 / Pressure Ratio
Compressor Pressure Ratio Effect
Increasing the pressure ratio (πc) improves thermal efficiency but requires higher turbine inlet temperature and increases compressor work.
Design Note
Modern aero-derivative gas turbines operate at pressure ratios of 30:1 to 40:1, while industrial turbines typically range from 10:1 to 25:1. Higher pressure ratios require advanced materials and cooling technologies.
03 / Turbine Inlet Temperature
TIT & Material Limits
Turbine inlet temperature (TIT) is the most limiting parameter in gas turbine design. Higher TIT improves efficiency but requires advanced cooling and materials.
Material Limits
04 / Mathematical Roots
Algorithm & Core Equations
The solver uses the Brayton cycle equations with component efficiencies to calculate performance parameters.
Governing Formula
Ideal compressor exit temp
Ambient temperature
Pressure ratio
Specific heat ratio
Governing Formula
Thermal efficiency
Turbine work
Compressor work
Heat input
// Constants
const GAMMA_AIR = 1.4;
const CP_AIR = 1005; // J/kg·K
const CP_GAS = 1148; // J/kg·K
const T_AMBIENT = 288.15; // 15°C
function solveBraytonCycle(
rp: number, // pressure ratio
tit: number, // turbine inlet temp (K)
mdot: number, // mass flow (kg/s)
etaC: number, // compressor efficiency
etaT: number, // turbine efficiency
) {
// Compressor
const rp_gamma = Math.pow(rp, (GAMMA_AIR - 1) / GAMMA_AIR);
const t2s = T_AMBIENT * rp_gamma;
const t2 = T_AMBIENT + (t2s - T_AMBIENT) / etaC;
const Wc = mdot * CP_AIR * (t2 - T_AMBIENT);
// Combustor (heat input)
const t3 = tit;
const Qin = mdot * CP_GAS * (t3 - t2);
// Turbine
const t4s = t3 / rp_gamma;
const t4 = t3 - etaT * (t3 - t4s);
const Wt = mdot * CP_GAS * (t3 - t4);
// Performance
const Wnet = Wt - Wc;
const etaTh = Wnet / Qin;
return { Wc, Wt, Wnet, etaTh, t4, t2, t2s, t4s, Qin };
}Engineering Scope & Limitations
Ideal Gas Assumption
The solver uses constant specific heats (air standard assumptions). Real gas effects would require more complex models.
Component Models
Compressor and turbine efficiencies are assumed constant. In reality, efficiency varies with operating conditions and speed.
Mechanical Losses
The model does not include gearbox losses, bearing friction, or auxiliary loads. These would reduce the net output.