✈️ Brayton Cycle (Gas Turbine)
Ideal and non-ideal Brayton cycle with optional regenerator. Compressor and turbine work, back-work ratio, and efficiency.
⚡ Fortran 90 Engine
Double Precision (IEEE 754)
✓ ISO / ASME Validated
📊 Solver Telemetry
● ACTIVE
👁️ Consultations
3,821
⚡ Calculs faits
3,047
💾 Téléchargements
412
📦 Code Fortran
11.4 KB
📅 Mise en service
Jan 2025
⏱️ Latence
< 1 ms
Gas Turbine Power Cycles
The Brayton cycle models the thermodynamic processes within a gas turbine engine. Adjust parameters like pressure ratio, component efficiencies, and optional modifications to evaluate performance.
• Regeneration: Uses turbine exhaust to preheat compressed air before entering the combustor.
• Intercooling: Splits compression into stages with cooling between to minimize compressor work.
• Reheat: Splits expansion into stages with heating between to maximize turbine output.
• Intercooling: Splits compression into stages with cooling between to minimize compressor work.
• Reheat: Splits expansion into stages with heating between to maximize turbine output.
📝 Configuration
Brayton Cycle Analysis:
• Compressor Work: W_c = Cp * (T_exit - T_in)
• Turbine Work: W_t = Cp * (T_in - T_exit)
• Net Power: P_net = ṁ * (W_t - W_c)
• Regenerator: heats compressor exit air with turbine exhaust.
• Intercooling/Reheating: utilizes multiple stages to reduce compressor input / increase turbine output.
Assumptions: Air standard ideal gas properties ($Cp = 1.005$ kJ/kg·K, $k = 1.4$).
• Compressor Work: W_c = Cp * (T_exit - T_in)
• Turbine Work: W_t = Cp * (T_in - T_exit)
• Net Power: P_net = ṁ * (W_t - W_c)
• Regenerator: heats compressor exit air with turbine exhaust.
• Intercooling/Reheating: utilizes multiple stages to reduce compressor input / increase turbine output.
Assumptions: Air standard ideal gas properties ($Cp = 1.005$ kJ/kg·K, $k = 1.4$).
📊 Results & Visualization
Configure inputs and click Analyze to view Brayton cycle performance.
📘 Calculation Methodology
Mathematical Model & Theory
The Brayton cycle serves as the fundamental thermodynamic model for gas turbine power plants. Thermal efficiency ($\eta_{th}$) is determined by net work output relative to heat inputs:
$$\eta_{th} = \frac{W_{net}}{Q_{in}} = \frac{W_t - W_c}{Q_{in}}$$
$$\varepsilon_{regen} = \frac{T_{regen,exit} - T_{comp,exit}}{T_{turb,exit} - T_{comp,exit}}$$
Assumptions & Cycle Idealizations
- Cold-air standard properties are assumed ($C_p = 1.005$ kJ/(kg·K), $\gamma = 1.4$)
- Isentropic compressor and turbine efficiencies ($\eta_c$, $\eta_t$)
- Zero piping friction or pressure drops
Literature References
- Cengel, Y. A., & Boles, M. A., Thermodynamics: An Engineering Approach, McGraw-Hill.
- Moran, M. J., Shapiro, H. N., Boettner, D. D., & Bailey, M. B., Fundamentals of Engineering Thermodynamics, Wiley.
Worked Engineering Example
Problem Statement:
An air-standard Brayton cycle operates at a pressure ratio $r_p = 8$. Compressor inlet is at 300 K and turbine inlet is at 1300 K. Find the ideal thermal efficiency.
Step-by-step Solution:
1. Apply cold air-standard efficiency formula ($\gamma = 1.4$):
$$\eta_{th} = 1 - \frac{1}{r_p^{(\gamma - 1)/\gamma}}$$ $$\eta_{th} = 1 - \frac{1}{8^{(1.4-1)/1.4}} = 1 - \frac{1}{8^{0.2857}} = 1 - 0.552 = 0.448 \quad (44.8\%)$$
Final Result:
Thermal efficiency is 44.8%.
An air-standard Brayton cycle operates at a pressure ratio $r_p = 8$. Compressor inlet is at 300 K and turbine inlet is at 1300 K. Find the ideal thermal efficiency.
Step-by-step Solution:
1. Apply cold air-standard efficiency formula ($\gamma = 1.4$):
$$\eta_{th} = 1 - \frac{1}{r_p^{(\gamma - 1)/\gamma}}$$ $$\eta_{th} = 1 - \frac{1}{8^{(1.4-1)/1.4}} = 1 - \frac{1}{8^{0.2857}} = 1 - 0.552 = 0.448 \quad (44.8\%)$$
Final Result:
Thermal efficiency is 44.8%.