1. Shaft Power Cycles Ideal cycles Assumptions:
Both compressor and turbine are isentropic (reversible adiabatic, η= 100 %)
Pressure losses in both of combustion chamber and heat exchanger are negligible.
Working fluid is air. It behaves as an ideal gas
Mass flow rate is constant and combustion process is replaced by heat addition process.
Changes of K.E. of the working fluid between inlet and outlet of each component are negligible.
Heat transfer in heat exchanger is complete (ε=100%)

2. Shaft Power Cycles Description of simple cycle Specific work, w
Thermal efficiency, η= w / q

3. Shaft Power Cycles
First law of thermodynamics (conservation of energy)
q – w = Δh
Compressor (adiabatic, q=0.)
Turbine

4. Shaft Power Cycles
Combustion chamber

5. Shaft Power Cycles

6. Shaft Power Cycles

7. Shaft Power Cycles

8. Simple cycle

9. Regeneration cycle (heat exchange cycle)
To benefit from the exhaust, a regenerator is used to reduce the heat addition, the efficiency is improved since heat rejection is reduced.

10. Regeneration cycle (heat exchange cycle)
Recall that .

11. Regeneration cycle (heat exchange cycle)

12. Reheat Cycle
In the reheat cycle, both of the heat addition and work done are increased. The thermal efficiency may increase or decrease depending on the values of T4 in comparison to T3.

13. Reheat Cycle For optimum conditions, i.e. maximum work, thus.
This gives

14. Reheat Cycle
Thus gives

15. Reheat Cycle
The efficiency is calculated as

16. Cycle with reheat and heat exchange
For ideal regenerator;

17. Methods for accounting for component losses
Performance of real cycles differ from ideal cycles for the following reasons:
Velocities in turbomachinery are high thus Δ K.E. is not equal to zero.
Compression and expansion are irreversible.
Friction losses in H.E. and CC.
H.E. effectiveness is less than 100%
Specific heat specific heat ratio are not constant through the cycle processes
More work is required for compression process to overcome bearings and friction in transmission between compressor and turbine
Cycle efficiency is different from unit efficiency
Some compressed air is bled for turbine blade cooling.

18. Stagnation properties
The energy equation for a flow coming to rest is
Where h is the static enthalpy O refers to the stagnation condition C is the velocity

19. Stagnation properties
Thus:

20. Stagnation properties
Thus the first law equation is

21. Compressor and turbine efficiency
Compressor efficiency

22. Compressor and turbine efficiency

23. Polytropic efficiency
Consider a compressor of different stages. The Polytropic efficiency (defined as the isentropic efficiency of an elemental stage in the process such that it is constant throughout the whole process) given by

24. Polytropic efficiency
For an expansion (such as a turbine)

25. Polytropic efficiency
For a compressor
For a turbine

26. Pressure losses

27. Heat exchanger effectiveness

28. Mechanical Losses and Variations in specific heats

29. Fuel Air ratio

30. Fuel Air ratio

31. Specific fuel consumption

32. Example 2.1 A heat exchange cycle having the following data:
turbine inlet temperature (K)
compressor pressure ratio 4.0
isentropic efficiency of compressor 0.85
isentropic efficiency of turbine 0.87
combustion efficiency
mechanical transmission efficiency 0.99
heat exchange effectiveness 0.80
ambient conditions 1(bar), 288 (k)
pressure losses
combustion chamber 2% of compressor delivery pressure
heat exchanger air side 3% of compressor delivery pressure
heat exchanger gas side (bar)

33. Example 2.1

34. Example 2.1

35. Example 2.1

36. Example 2.1

37. Example 2.1: Using EES

38. Example 2.1: Using EES

39. Example 2.1: Using EES

40. Example 2.2
A simple gas turbine with free turbine power having the following data:
turbine inlet temperature (K)
compressor pressure ratio
isentropic efficiency of compressor 0.86
isentropic efficiency of each turbine 0.89
combustion efficiency
mechanical efficiency of each shaft 0.99
ambient conditions 1(bar), 288 (k)
combustion chamber pressure loss 6% comp. deliv. pres.
exhaust pressure loss (bar)

41. Example 2.2

42. Example 2.2

43. Example 2.2

44. Example 2.2

45. Example 2.3 net work output 240 MW turbine inlet temperature 1525(K)
Reheat Cycle
net work output MW
turbine inlet temperature (K)
compressor pressure ratio 30
polytropic efficiency for compressor and turbines
0.89
Pressure loss in first combustor is 2%
Pressure loss in second combustor 4%
exhaust pressure (bar)
ambient conditions 288(K), 1.01(bar)
Assume that pressure ratios in HP and LP turbines are equal

46. Example 2.3

47. Example 2.3

48. Example 2.3