🔥 Brayton Cycle Calculator
Analyze gas turbine power plants. Evaluate thermal efficiency and work output with regeneration, reheating, and intercooling options.
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%.