2. chapter 8 Gas Power Cycle

3. 8-1 The Analysis of a Cycle 8-1-1 The average temperature of a process We define: That is: 1 2 T s s1s1 s2s2 T

4. 8-1-2 The Analysis of a Cycle 1 2 T s s1s1 s2s2 As to a cycle: a b T2T2 T1T1

5. 8-2 Otto Cycle 8-2-1 N. A. Otto Nicolaus August Otto the inventor of the four-stroke cycle was born on 14th June 1831 in Germany. In 1862 he began first experiments with four-strokes engines. The first four-stroke engines is shown. they correspond to the today's engines. He died on 26th January 1891 in Cologne

6. 8-2-2 The Cycle - The Four Strokes Intake stroke: The piston moves down the cylinder and the pressure will drop (negative pressure). The intake valve is opend. Because of the low pressure the air/fuel mixtures is sucked into the cylinder.

7. Compression stroke: At Bottom Dead Center (BDC) the cylinder is at its maximum volume and the intake valve is closed. Now the piston moves backward the Top Dead Center (TDC) and compresses the air/fuel mixtures.

8. Near the end of the compression stroke, the ignition starts the combustion and the mixture burns very rapidly. The expanding gas creates a high pressures against the top of the piston.

9. Power stroke The force drives the piston downward to crank shaft (the valves are closed). The volume is increased and the pressure is decreased. No more energy is added and because of this the internal energy of the gas is decreased as so as the temperature.

10. Exhaust stroke At BDC the exhaust valve is opened and the piston moves up the cylinder. The pressure drops near the pressure outside the cylinder because of the opened exhaust valve. Exhaust gas leaves the cylinder. The volume is decreased.

11. The theory cycle 1 2 3 4 5 p v 8-2-3 The Cycle - The Four Strokes Adiabatic process

12. Theory efficiency of Otto cycle Then ：

13. ε compression ratio

14. 8-3 Diesel Cycle 8-2-1 Rudolf Diesel Rudolf Diesel (1858 – 1913) was born in Paris in 1858. After graduation he was employed as a refrigerator engineer. However, his true love was in engine design. In 1893, he published a paper describing an engine with combustion within a cylinder, the internal combustion engine. In 1894, he filed for a patent for his new invention, the diesel engine. Diesel was almost killed by his engine when it exploded - however, his engine was the first that proved that fuel could be ignited without a spark. He operated his first successful engine in 1897.

17. 8-3-2 The Diesel Cycle

18. 8-3-3 The Efficiency of Diesel Cycle The theory cycle 1 23 4 5 p v

19. Theory efficiency of Diesel cycle We define

20. Since process 1-4 has a constant volume

21. To increase efficiency: 1 23 4 5 p v The compression pressure should be higher The volume increase should be smaller

22. Other internal combustion engine

23. 8-4-1 The Equipments of Brayton Cycle 8-4 Brayton Cycle

26. Advantages Gas turbine engines are smaller than their reciprocating counterparts of the same power Gas turbine engines have a great power-to-weight ratio compared to reciprocating engines. That is, the amount of power you get out of the engine compared to the weight of the engine itself is very good.

28. 8-4-2 Brayton Cycle T s 1 2 3 4 Constant pressure p v 1 2 3 4 adiabatic

29. 8-4-3 Efficiency of Brayton Cycle

31. 8-4-3 The Optimum Compression Ratio T s 1 2 3 4 T max the compression ratio will be increased to get high efficiency But the power ratio will decrease 3’3’ 4’4’ If T 3 is limited:

32. We have to compromise between high efficiency and high power ratio. Usually in aerospace field the power ratio is more important T s T max T0T0 Obviously there must be an optimum compression ratio which makes the cycle has maximum power ratio

33. This ratio is denoted as: ε max The efficiency depends on T 3 basically

34. 8-4-4 The methods to increase the efficiency (1) Regenerative Brayton Cycle T s T2T2 T1T1 T2T2 T1T1

35. Engine Characteristic TypeTwin-Spool, Augmented Turbofan ApplicationF-22 Advanced Tactical Fighter Thrust35,000 Pound Thrust Class Engine ControlFull-Authority Digital Electronic Control Compression System Twin Spool/Counter Rotating/Axial Flow/ Low-Aspect Ratio Three-Stage Fan Six-Stage Compressor CombustorAnnular Turbine Axial Flow/Counter Rotating One-Stage, High-Pressure Turbine One-Stage, Low-Pressure Turbine Nozzle Two-dimensional Vectoring Convergent/Divergent

36. oil Combustion chamber Air in compressor gas turbine regenerator

37. (2) Isothermal compression and regenerative cycle T s

38. 8-5 Jet Engine Engine Characteristic TypeTwin-Spool, Augmented Turbofan ApplicationF-22 Advanced Tactical Fighter Thrust35,000 Pound Thrust Class Engine ControlFull-Authority Digital Electronic Control Compression System Twin Spool/Counter Rotating/Axial Flow/ Low-Aspect Ratio Three-Stage Fan Six-Stage Compressor CombustorAnnular Turbine Axial Flow/Counter Rotating One-Stage, High-Pressure Turbine One-Stage, Low-Pressure Turbine Nozzle Two-dimensional Vectoring Convergent/Divergent

39. T s 1 2 3 4 5 6 1 2 3456

42. The methods to increase the power ratio of jet engine (1) After burning After burner

43. T s 1 2 3 4 5 6 7

44. (2) Increase T 4 T s 1 2 3 4’4’ 5’5’ 6’6’ 4 6

45. 8-5 The Stirling Cycle p v 1 2 3 4 T s 1 2 3 4

46. The End Of This Chapter Thank You