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MD 9 (usually air or gas). 69 OS, ae arenes 69 DU obeo 966 + The two major gas power cycles discussed are: © Camot Cycle (Theoretical maximum efficiency) © Brayton Cycle (Practical gas turbine cycle) 2,Carnot Cycle (Idealized Gas Power Cycle) ‘Developed by Sadi Carnot (1824), this cycle provides a theoretical upper limit on efficiency. «It consists of four reversible processes. Processes in the Carnot Cycle 1 Isothermal Expansion (1 —> 2), © Heat Qin is added at a constant high temperature 7; Had Bboaidan® ovo Goon O © The gas expands and perfgns wk onthe surroundings Boa Bebo F ‘Aba DH XD OS 2. ‘Adiabatic Expansion (2 > 3) co The gas expands further without heat transfer. DP? BDI OOD Bobdloo MD. © Its temperature decreases from T; to T. Abowd? TT Ber 3. Isothermal Compression (3+ 4) | © Heat Quy is rejected at constant low temperature Ty, eon 3 Gdronrve OD wne Qoriov ‘Scanned with |CamScanner@ Soa cond OO © Thegas is compressed, losing eneray 4. ‘Adiabatic Compression (4+ 1) © The gas is further compressed without heat transfer, m0 BD MOY O92 sPs00% @BSErc A+ ‘© Its temperature rises back to Ty BG Cdbow2 nyo Ten Olae wv Limitations of the Carnot Cycle * Not practical for real engines due to: BD DBA DED Heo ao 1. Fries processes % {impossible @ ns 2. Heat cangot transfer wit out a temperature diffe Lo BODaM GOED nS ee myambe Cor 3. Sothermal expafBion Compression requites very Sow operation, which is impractical. 4% O8 cox ar! 4200260 3Bravton Cycle (Practical Gas Turbine Cycle) ‘+ The Brayton cycle is used in gas turbines for power plant, jet engines, and industrial applications. ‘© It operates on a continuous flow system, unlike the Camot eycle. 82 Corre’ oOo 00D BONO God SEDAN Oo Bay Processes in the Brayton Cycle 1 Compression (1 — 2) © Airis compressed ina compressor. 20.0 agbaman we, e882 6 co Pressure and temperature increase. Py T (Y 2. Constant Pressure Heat Addition (2 3)/ co Heat is added at constant pressure in the combustion chamber. Bod B20 6dr) Gadd © Temperature rises significantly. T axOOa Oe Oe are ce 3 Adiabatic Expansion (3 4) © The hot air expands in the turbine, producing work output Ciogp Doa Qanbbo S 22 gee moa ‘Scanned with |CamScanner‘© Temperature and pressure drop. @v'T &B@ 4 (Constant Pressure Heat Rejection (4 — 1) © Heat is rejected to the surroundings, cooling the gas before re-entering the cycle, BBBOOS roe 22> wh: Comparison: Camot Cycle vs. Brayton Cycle Feature Camot Cycle | Brayton Cycle Efficiency | Theoretically highest | Lower but practical | Heat Transfer Isothermal | Constant pressure Work Process | Reversible Continuous flow Application | Theoretical | Gas turbines, jet engines 4 Actual Brayton Cycle (Real-World Adiustnents), © Inreal gas turbines, the actual cycle differs due to irreversibilities such as: prec 03 Ob69n 90 Hz) MbI® Oooo Hw BBO © Friction hd D- o. Pressure losses © Non-ideal heat transfer Deviations from the Ideal Brayton Cycle ‘* Compression is not isentropic (irreversible compression due to friction), aboroo od Expansion in the turbine is not isentropic (energy losses in turbine blades). POP AMG Y DO ‘+ Pressure losses occur in the combustion chamber. ego B08 BA wD. ‘Scanned with |CamScannerModifications to Improve Efficiency 1 Imercooting | ‘© Used between compressor stages to reduce work required ig compression. MOD Deo) G22 ovo. DO ‘© Advantage: Reduces compressor work, improving efficiency, DBIOG 10 BAm@d8 , bor AON 2D Hdd, © Disadvantage: Requires additional cooling equipment. 98689 BS O0 (Cad F200. i 2 ©. Used between turbine stages o increase work output. DEo20 VD DS ‘3 © Advantage: Increases power output. ‘© Disadvantage: Additional fuel consumption, BOELO Yao Forvod 3. Regeneration! © Uses exhaust heat to preheat air before entering the combustion chamber. One AB YD mI 2%SODO 02b Ave 64 esd © Advantage: Reduces fuel consumption and increases cycle efficiency. Q- WB ovdvo YD. © Disadvantage: Increases system complexity. + F082 BocHbtocr —5.Practical Applications, © Camot Cycle is used as a theoretical benchmark but not in real systems. ‘© Brayton Cycle is the foundation of gas turbines, used in: ©. Jetengines © Power plants © Industrial gas turbines ‘Scanned with |CamScannerMethods to Improve Gas Turbine Performance Method] Purpose Effect on Efficiency Intercooling | Reduces compressor work | Moderate improvement Reheating | Increases turbine work | Moderate improvement Regeneration | Reuses exhaust heat ‘Significant improvement Conclusion ‘© Gas power cycles are essential in modem energy conversion systems. © The Camot cycle is ideal but impractic ‘world applications. + Efficiency improvements (intercooling, reheating, regeneration) enhance practical gas turbines. ‘ The’Brayton cycle is the foundation of modem power generation and aviation propulsion systems. 31, while the Brayton cycle is used in real- Scanned with |\CamScanner