Engineering webinar material dealing with simple and basic Brayton Cycle and power cycle components/processes and their T - s diagrams, ideal and real operation and major performance trends when air is considered as the working fluid.

1. Engineering Software
P.O. Box 2134
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Phone: (301) 919-9670
E-Mail: info@engineering-4e.com
http://www.engineering-4e.com
Copyright © 1996

2. Energy Conversion Ideal vs Real Operation
Analysis Webinar Objectives
In this webinar, the engineering students and professionals get familiar with the simple
and basic power cycles, power cycle components/processes and compressible flow
and their T - s, p - V and h - T diagrams, ideal vs real operation and major
performance trends when air is considered as the working fluid.
Performance Objectives:
Introduce basic energy conversion engineering assumptions and equations
Know basic elements of Carnot Cycle, Brayton Cycle, Otto Cycle, Diesel Cycle,
compression, combustion and expansion processes and compressible flow (nozzle,
diffuser and thrust) and their T - s, p - V and h - T diagrams
Be familiar with Carnot Cycle, Brayton Cycle, Otto Cycle, Diesel Cycle, compression,
combustion, expansion and compressible flow (nozzle, diffuser and thrust) ideal vs
real operation
Understand general Carnot Cycle, Brayton Cycle, Otto Cycle, Diesel Cycle,
compression, combustion, expansion and compressible flow (nozzle, diffuser and
thrust) performance trends

3. This webinar consists of the following three major sections:
• Power Cycles (Carnot, Brayton, Otto and Diesel)
• Power Cycle Components/Processes (compression,
combustion and expansion)
• Compressible Flow (nozzle, diffuser and thrust)
In this webinar, first overall engineering assumptions and basic engineering
equations are provided. Furthermore, for each major section, basic
engineering equations, section material and conclusions are provided.
Energy Conversion Analysis Webinar

4. The energy conversion analysis presented in this webinar considers ideal (isentropic) vs real operation and the
working fluid is air. Furthermore, the following assumptions are valid:
Power Cycles
Single species consideration -- fuel mass flow rate is ignored and its impact on the properties of the working
fluid
Basic equations hold (continuity, momentum and energy equations)
Specific heat is constant
Power Cycle Components/Processes
Single species consideration
Basic equations hold (continuity, momentum and energy equations)
Specific heat is constant
Compressible Flow
Single species consideration
Basic equations hold (continuity, momentum and energy equations)
Specific heat is constant
Thermodynamic and Transport Properties
Single species consideration
Ideal gas approach is used (pv=RT)
Specific heat is not constant
Coefficients describing thermodynamic and transport properties were obtained from the NASA Glenn Research
Center at Lewis Field in Cleveland, OH -- such coefficients conform with the standard reference temperature of
298.15 K (77 F) and the JANAF Tables
Engineering Assumptions

5. Basic Conservation Equations
Continuity Equation
m = ρvA [kg/s]
Momentum Equation
F = (vm + pA)out - in [N]
Energy Equation
Q - W = ((h + v2/2 + gh)m)out - in [kW]
Basic Engineering Equations

6. Ideal Gas State Equation
pv = RT [kJ/kg]
Perfect Gas
cp = constant [kJ/kg*K]
Kappa
χ = cp/cv [/]
For air: χ = 1.4 [/], R = 0.2867 [kJ/kg*K] and
cp = 1.004 [kJ/kg*K]
Basic Engineering Equations

7. Power Cycles Engineering Equations
Carnot Cycle Efficiency
 = 1 - TR/TA
Otto Cycle Efficiency
 = (cv(T3 - T2) - cv(T4 - T1))/(cv(T3 - T2))
Brayton Cycle Efficiency
 = (cp(T3 - T2) - cp(T4 - T1))/(cp(T3 - T2))
Diesel Cycle Efficiency
 = (cp(T3 - T2) - cv(T4- T1))/(cp(T3 - T2))
Cycle Efficiency
 = Wnet/Q [/]
Heat Rate
HR = (1/)3,412 [Btu/kWh]
rp = p2/p1 [/]; ε = V1/V2 [/]; φ = V3/V2 [/]

8. Power Cycles Engineering Equations
Otto Cycle
wnet = qh - ql = cv(T3 - T2) - cv(T4 - T1) [kJ/kg]
Wnet = wnetm [kW]
Brayton Cycle
wnet = qh - ql = cp(T3 - T2) - cp(T4 - T1) [kJ/kg]
Wnet = wnetm [kW]
Diesel Cycle
wnet = qh - ql = cp(T3 - T2) - cv(T4 - T1) [kJ/kg]
Wnet = wnetm [kW]

9. Carnot Cycle Schematic Layout
Compressor
Heat Exchanger
Gas Turbine
1
32
4
Heat Addition
Heat Exchanger
Heat Rejection
Carnot Cycle

10. Carnot Cycle T - s Diagram
1
32
4
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Carnot Cycle

11. Carnot Cycle Efficiency
0
20
40
60
80
500 600 700 800 900 1,000
CarnotCycleEfficiency[%]
Heat Addition Temperature [K]
Compressor Inlet Temperature: 298 [K]
Carnot Cycle

12. Carnot Cycle Efficiency
0
20
40
60
80
278 288 298 308 318 328
CarnotCycleEfficiency[%]
Heat Rejection Temperature [K]
Turbine Inlet Temperature: 800 [K]
Carnot Cycle

13. Brayton Cycle (Gas Turbine) Schematic Layout -- Open Cycle
Compressor
Combustor
Gas Turbine
1
32
4
Fuel
Brayton Cycle (Gas Turbine)
Heat Addition
Working Fluid In Working Fluid Out

14. Brayton Cycle Schematic Layout -- Closed Cycle
Compressor
Heat Exchanger
Gas Turbine
1
32
4
Heat Addition
Heat Exchanger
Heat Rejection
Brayton Cycle (Gas Turbine)

15. Brayton Cycle (Gas Turbine) T - s Diagram
1
3
2s
4s
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Brayton Cycle (Gas Turbine)
2
4

16. Brayton Cycle (Gas Turbine) Efficiency
0
20
40
60
80
5 10 15 20 25
Compression Ratio (P2/P1) [/]
BraytonCycle(GasTurbine)Efficiency[%]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Compression Efficiency [%]
Ambient Temperature: 298 [K] -- Gas Turbine Inlet Temperature: 1,500 [K]

17. Brayton Cycle (Gas Turbine) Specific Power
Output
0
100
200
300
400
500
900 1,200 1,500
Gas Turbine Inlet Temperature [K]
BraytonCycle(GasTurbine)SpecificPower
Output[kJ/kg]
85 90 95 100
Working Fluid: Air
Compressor Inlet Temperature: 298 [K] -- Gas Turbine Inlet Pressure: 15 [atm]
Brayton Cycle (Gas Turbine)
Isentropic Compression Efficiency [%]
Compression Ratio (P2/P1) = 15 [/]

18. Brayton Cycle (Gas Turbine) Power Output
0
25
50
75
100
50 100 150
Working Fluid Mass Flow Rate [kg/s]
BraytonCycle(GasTurbine)PowerOutput[MW]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Compression Efficiency [%]
Gas Turbine Inlet Temperature: 1,500 [K] -- Gas Turbine Inlet Pressure: 15 [atm]
Compression Ratio (P2/P1) = 15 [/]

19. Brayton Cycle (Gas Turbine) Efficiency
0
20
40
60
80
5 10 15 20 25
Compression Ratio (P2/P1) [/]
BraytonCycle(GasTurbine)Efficiency[%]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Expansion Efficiency [%]
Ambient Temperature: 298 [K] -- Gas Turbine Inlet Temperature: 1,500 [K]

20. Brayton Cycle (Gas Turbine) Specific Power
Output
0
100
200
300
400
500
900 1,200 1,500
Gas Turbine Inlet Temperature [K]
BraytonCycle(GasTurbine)SpecificPower
Output[kJ/kg]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Expansion Efficiency [%]
Compressor Inlet Temperature: 298 [K] -- Gas Turbine Inlet Pressure: 15 [atm]
Compression Ratio (P2/P1) = 15 [/]

21. Brayton Cycle (Gas Turbine) Power Output
0
25
50
75
100
50 100 150
Working Fluid Mass Flow Rate [kg/s]
BraytonCycle(GasTurbine)PowerOutput[MW]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Expansion Efficiency [%]
Compression Ratio (P2/P1) = 15 [/]
Gas Turbine Inlet Temperature: 1,500 [K] -- Gas Turbine Inlet Pressure: 15 [atm]

22. Brayton Cycle (Gas Turbine) Efficiency
0
20
40
60
80
5 10 15 20 25
Compression Ratio (P2/P1) [/]
BraytonCycle(GasTurbine)Efficiency[%]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Compression and Expansion Efficiency [%]
Ambient Temperature: 298 [K] -- Gas Turbine Inlet Temperature: 1,500 [K]

23. Brayton Cycle (Gas Turbine) Specific Power
Output
0
100
200
300
400
500
900 1,200 1,500
Gas Turbine Inlet Temperature [K]
BraytonCycle(GasTurbine)SpecificPower
Output[kJ/kg]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Compression and Expansion Efficiency [%]
Compressor Inlet Temperature: 298 [K] -- Gas Turbine Inlet Pressure: 15 [atm]
Compression Ratio (P2/P1) = 15 [/]

24. Brayton Cycle (Gas Turbine) Power Output
0
25
50
75
100
50 100 150
Working Fluid Mass Flow Rate [kg/s]
BraytonCycle(GasTurbine)PowerOutput[MW]
85 90 95 100
Working Fluid: Air
Brayton Cycle (Gas Turbine)
Isentropic Compression and Expansion Efficiency [%]
Compression Ratio (P2/P1) = 15 [/]
Gas Turbine Inlet Temperature: 1,500 [K] -- Gas Turbine Inlet Pressure: 15 [atm]

25. Otto Cycle p - V Diagram
1
3
2s
4s
Pressure--p[atm]
Volume -- V [m^3]
Otto Cycle

26. Otto Cycle T - s Diagram
1
3
2s
4s
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Otto Cycle
2
4

27. Otto Cycle Efficiency
0
20
40
60
80
2.5 5 7.5 10 12.5
Compression Ratio (V1/V2) [/]
OttoCycleEfficiency[%]
85 90 95 100
Working Fluid: Air
Otto Cycle
Isentropic Compression Efficiency [%]
Ambient Temperature: 298 [K] -- Combustion Temperature: 1,200 [K]

28. Otto Cycle Power Output
0
100
200
300
400
1,200 1,500 1,800
Combustion Temperature [K]
OttoCyclePowerOutput[kW]
85 90 95 100
Compression Ratio (V1/V2) = 10 [/]
Working Fluid: Air
Ambient Temperature: 298 [K] -- Number of Revolutions: 60 [1/s]
For Given Geometry of the Four Cylinder and Four Stroke Otto Engine
Otto Cycle
Isentropic Compression Efficiency [%]

29. Otto Cycle Efficiency
0
20
40
60
80
2.5 5 7.5 10 12.5
Compression Ratio (V1/V2) [/]
OttoCycleEfficiency[%]
85 90 95 100
Working Fluid: Air
Otto Cycle
Isentropic Expansion Efficiency [%]
Ambient Temperature: 298 [K] -- Combustion Temperature: 1,200 [K]

30. Otto Cycle Power Output
0
100
200
300
400
1,200 1,500 1,800
Combustion Temperature [K]
OttoCyclePowerOutput[kW]
85 90 95 100
Compression Ratio (V1/V2) = 10 [/]
Working Fluid: Air
Ambient Temperature: 298 [K] -- Number of Revolutions: 60 [1/s]
For Given Geometry of the Four Cylinder and Four Stroke Otto Engine
Otto Cycle
Isentropic Expansion Efficiency [%]

31. Otto Cycle Efficiency
0
20
40
60
80
2.5 5 7.5 10 12.5
Compression Ratio (V1/V2) [/]
OttoCycleEfficiency[%]
85 90 95 100
Working Fluid: Air
Otto Cycle
Isentropic Compression and Expansion Efficiency [%]
Ambient Temperature: 298 [K] -- Combustion Temperature: 1,200 [K]

32. Otto Cycle Power Output
0
100
200
300
400
1,200 1,500 1,800
Combustion Temperature [K]
OttoCyclePowerOutput[kW]
85 90 95 100
Compression Ratio (V1/V2) = 10 [/]
Working Fluid: Air
Ambient Temperature: 298 [K] -- Number of Revolutions: 60 [1/s]
For Given Geometry of the Four Cylinder and Four Stroke Otto Engine
Otto Cycle
Isentropic Compression and Expansion Efficiency [%]

33. Diesel Cycle p - V Diagram
1
32s
4s
Pressure--p[atm]
Volume -- V [m^3]
Diesel Cycle

34. Diesel Cycle T - s Diagram
1
3
2s
4s
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Diesel Cycle
2
4

35. Diesel Cycle Efficiency
0
20
40
60
80
7.5 10 12.5 15 17.5
Compression Ratio (V1/V2) [/]
DieselCycleEfficiency[%]
85 90 95 100
Working Fluid: Air
Diesel Cycle
Isentropic Compression Efficiency [%]
Ambient Temperature: 298 [K]
Combustion Temperature: 1,800 [K]

36. Diesel Cycle Power Output
0
200
400
600
7.5 10 12.5 15 17.5
Compression Ratio (V1/V2) [/]
DieselCyclePowerOutput[kW]
85 90 95 100
Combustion Temperature: 1,800 [K]
Working Fluid: Air
Ambient Temperature: 298 [K] -- Number of Revolutions: 60 [1/s]
For Given Geometry of the Four Cylinder and Four Stroke Diesel Engine
Diesel Cycle
Isentropic Compression Efficiency [%]

37. Diesel Cycle Efficiency
0
20
40
60
80
7.5 10 12.5 15 17.5
Compression Ratio (V1/V2) [/]
DieselCycleEfficiency[%]
85 90 95 100
Working Fluid: Air
Diesel Cycle
Isentropic Expansion Efficiency [%]
Ambient Temperature: 298 [K]
Combustion Temperature: 1,800 [K]

38. Diesel Cycle Power Output
0
200
400
600
7.5 10 12.5 15 17.5
Compression Ratio (V1/V2) [/]
DieselCyclePowerOutput[kW]
85 90 95 100
Diesel Cycle
Isentropic Expansion Efficiency [%]
Combustion Temperature: 1,800 [K]
Working Fluid: Air
Ambient Temperature: 298 [K] -- Number of Revolutions: 60 [1/s]
For Given Geometry of the Four Cylinder and Four Stroke Diesel Engine

39. Diesel Cycle Efficiency
0
20
40
60
80
7.5 10 12.5 15 17.5
Compression Ratio (V1/V2) [/]
DieselCycleEfficiency[%]
85 90 95 100
Working Fluid: Air
Diesel Cycle
Isentropic Compression and Expansion Efficiency [%]
Ambient Temperature: 298 [K]
Combustion Temperature: 1,800 [K]

40. Diesel Cycle Power Output
0
200
400
600
7.5 10 12.5 15 17.5
Compression Ratio (V1/V2) [/]
DieselCyclePowerOutput[kW]
85 90 95 100
Diesel Cycle
Isentropic Compression and Expansion Efficiency [%]
Combustion Temperature: 1,800 [K]
Working Fluid: Air
Ambient Temperature: 298 [K] -- Number of Revolutions: 60 [1/s]
For Given Geometry of the Four Cylinder and Four Stroke Diesel Engine

41. Diesel Cycle Cut Off Ratio
0
1
2
3
4
7.5 10 12.5 15 17.5
Compression Ratio (V1/V2) [/]
DieselCycleCutOffRatio[/]
100
Diesel Cycle
Isentropic Compression and Expansion Efficiency [%]
Combustion Temperature: 1,800 [K]
Working Fluid: Air
Ambient Temperature: 298 [K] -- Number of Revolutions: 60 [1/s]
For Given Geometry of the Four Cylinder and Four Stroke Diesel Engine

42. Power Cycles Conclusions
The Carnot Cycle efficiency increases with an increase in the heat addition temperature when the heat rejection
temperature does not change at all. Furthermore, the Carnot Cycle efficiency decreases with an increase in the
heat rejection temperature when the heat addition temperature does not change at all. The Carnot Cycle
efficiency is not dependent on the working fluid properties.
The Brayton Cycle efficiency depends on the compression ratio values . The efficiency increases with an
increase in the compression ratio values for a fixed gas turbine inlet temperature. The Brayton Cycle specific
power output increases with an increase in the gas turbine inlet temperature for a fixed compression ratio.
Furthermore, the increase is greater for the higher gas turbine inlet temperature values.
The Brayton Cycle power output increases with an increase in the working fluid mass flow rate. The increase is
greater for the higher working fluid mass flow rate values for the fixed gas turbine inlet temperature and
compression ratio values.
The Otto Cycle efficiency increases with an increase in the compression ratio values for a fixed combustion
temperature. Also, the Otto Cycle power output increases with an increase in the combustion temperature for a
fixed compression ratio value and given geometry of the four cylinder and four stroke Otto engine.
The Diesel Cycle efficiency increases with an increase in the compression ratio and with a decrease in the cut
off ratio values for a fixed combustion temperature. Also, the Diesel Cycle power output increases with an
increase in the compression ratio values for a fixed combustion temperature value and given geometry of the
four cylinder and four stroke Diesel engine.
In general, as the isentropic compression and expansion efficiency values decrease, the cycle efficiency
decreases too.

43. Isentropic Compression
T2s/T1 = (p2/p1)(χ-1)/χ [/]
T2s/T1 = (V1/V2s)(χ-1) [/]
p2/p1 = (V1/V2s)χ [/]
wc = cp(T2 - T1) [kJ/kg]
Wc = cp(T2 - T1)m [kW]
c = (T2s - T1)/(T2 - T1) [/]
Power Cycle Components/Processes
Engineering Equations

44. Combustion is complete with and without heat loss and at
stoichiometric and stoichiometry > 1 conditions having different
oxidant preheat temperature and the oxidant is air.
Also,
Ideal Flame Temperature [K]
hreactants = hproducts [kJ/kg]
Real Flame Temperature [K]
hproducts = hreactants - heat loss [kJ/kg]
heat loss = (1 - combustion )HHV/(1 + oxidant to fuel ratio) [kJ/kg]
Power Cycle Components/Processes
Engineering Equations

45. Isentropic Expansion
T1/T2s = (p1/p2)(χ-1)/χ [/]
T1/T2s = (V2s/V1)(χ-1) [/]
p1/p2 = (V2s/V1)χ [/]
we = cp(T1 - T2) [kJ/kg]
We = cp(T1 - T2)m [kW]
e = (T1 - T2)/(T1 - T2s) [/]
Power Cycle Components/Processes
Engineering Equations

46. Compression Schematic Layout
Working Fluid In
Working Fluid Out
Compressor
1
2
Compression

47. Compression T - s Diagram
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Compression
2s
1
2

48. Compression Specific Power Input
100
200
300
400
500
5 10 15
Compression Ratio (P2/P1) [/]
CompressionSpecificPowerInput[kJ/kg]
85 90 95 100
Working Fluid: Air
Compressor Inlet Temperature: 298 [K] -- Ambient Pressure: 1 [atm]
Compression
Isentropic Compression Efficiency [%]

49. Compression Power Input
0
25
50
75
100
50 100 150
Working Fluid Mass Flow Rate [kg/s]
CompressionPowerInput[MW]
85 90 95 100
Working Fluid: Air
Compressor Inlet Temperature: 298 [K] -- Compression Ratio (P2/P1): 15 [/]
Compression
Isentropic Compression Efficiency [%]

50. Combustion Schematic Layout
Fuel
Oxidant -- Air
Combustion Products
Combustion

51. Specific Enthalpy vs Temperature
-20,000
-10,000
0
10,000
20,000
30,000
40,000
50,000
60,000
70,000
80,000
90,000
500 800 1,100 1,400 1,700 2,000 2,300 2,600 2,900 3,200 3,500 3,800 4,100 4,400 4,700 5,000
C(S) H2 S(S) N2 O2 H2O(L) CH4 CO2 H2O SO2
Combustion
SpecificEnthalpy[kJ/kg]
Temperature [K]

52. Combustion h - T Diagram
SpecificEnthalpy--h[kJ/kg]
Temperature -- T [K]
Reactants
Products
TflameTreference
Combustion
Heat Loss
Ideal
Real

53. Combustion
Oxidant Composition
Fuel Composition
C
[kg/kg]
1.000
0.000
0.000
0.780
0.860
-
H
[kg/kg]
0.000
1.000
0.000
0.050
0.140
-
S
[kg/kg]
0.000
0.000
1.000
0.030
0.000
-
N
[kg/kg]
0.000
0.000
0.000
0.040
0.000
-
O
[kg/kg]
0.000
0.000
0.000
0.080
0.000
-
H2O
[kg/kg]
0.000
0.000
0.000
0.020
0.000
-
CH4
[kg/kg]
-
-
-
-
-
1.000
Fuel
Carbon
Hydrogen
Sulfur
Coal
Oil
Gas
N
[kmol/kmol]
0.790
O
[kmol/kmol]
0.210
N
[kg/kg]
0.767
O
[kg/kg]
0.233
Oxidant
Air

54. Combustion
CO2
[kg/kg]
0.295
0.000
0.000
0.249
0.202
0.151
H2O
[kg/kg]
0.000
0.255
0.000
0.041
0.080
0.124
SO2
[kg/kg]
0.000
0.000
0.378
0.005
0.000
0.000
N2
[kg/kg]
0.705
0.745
0.622
0.705
0.718
0.725
O2
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
CO2
[kmol/kmol]
0.210
0.000
0.000
0.170
0.132
0.095
Fuel
Carbon
Hydrogen
Sulfur
Coal
Oil
Gas
SO2
[kmol/kmol]
0.000
0.000
0.210
0.002
0.000
0.000
N2
[kmol/kmol]
0.790
0.653
0.790
0.759
0.739
0.715
Combustion Products Flame Temperature, Stoichiometric Oxidant to Fuel Ratio and HHV
Flame Temperature
[K]
2,460
2,525
1,972
2,484
2,484
2,327
Stoichiometric
Oxidant to Fuel Ratio
[/]
11.444
34.333
4.292
10.487
14.649
17.167
HHV
[Btu/lbm]
14,094
60,997
3,982
14,162
20,660
21,563
Fuel
Carbon
Hydrogen
Sulfur
Coal
Oil
Gas
H2O
[kmol/kmol]
0.000
0.347
0.000
0.068
0.129
0.190
O2
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
Stoichiometric Combustion
Combustion Products Composition on Weight and Mole Basis

55. Combustion
Carbon
[K]
2,460
2,361
2,262
2,163
Hydrogen
[K]
2,525
2,409
2,293
2,176
Sulfur
[K]
1,972
1,895
1,818
1,741
Coal
[K]
2,484
2,381
2,278
2,174
Oil
[K]
2,484
2,381
2,275
2,168
Gas
[K]
2,327
2,236
2,145
2,053
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Flame Temperature, Stoichiometric Oxidant to Fuel Ratio and HHV
Ideal
Flame Temperature
[K]
2,460
2,525
1,972
2,484
2,484
2,327
Stoichiometric
Oxidant to Fuel Ratio
[/]
11.444
34.333
4.292
10.487
14.649
17.167
HHV
[Btu/lbm]
14,094
60,997
3,982
14,162
20,660
21,563
Fuel
Carbon
Hydrogen
Sulfur
Coal
Oil
Gas
Stoichiometric Combustion
Combustion Products Ideal vs Real Flame Temperature

56. Combustion Products -- Weight Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kg/kg]
Carbon Hydrogen Sulfur Coal Oil Gas
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]

57. Combustion Products -- Mole Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kmol/kmol]
Carbon Hydrogen Sulfur Coal Oil Gas
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]

58. Combustion Products Flame Temperature
1,900
2,000
2,100
2,200
2,300
2,400
2,500
2,600
Carbon Hydrogen Sulfur Coal Oil Gas
Flame Temperature [K]
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
FlameTemperature[K]

59. Combustion Products Flame Temperature
1,600
1,800
2,000
2,200
2,400
2,600
2,800
Carbon Hydrogen Sulfur Coal Oil Gas
FlameTemperature[K]
85 90 95 100
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Combustion Efficiency [%]

60. Combustion Stoichiometric Oxidant to Fuel Ratio
0
5
10
15
20
25
30
35
40
Carbon Hydrogen Sulfur Coal Oil Gas
Stoichiometric Oxidant to Fuel Ratio [/]
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
StoichiometricOxidanttoFuelRatio[/]

61. Higher Heating Value (HHV)
0
10,000
20,000
30,000
40,000
50,000
60,000
70,000
Carbon Hydrogen Sulfur Coal Oil Gas
HHV [Btu/lbm]
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
HHV[Btu/lbm]

62. Combustion
Oxidant Composition
Fuel Composition
C
[kg/kg]
1.000
0.000
0.000
0.780
0.860
-
H
[kg/kg]
0.000
1.000
0.000
0.050
0.140
-
S
[kg/kg]
0.000
0.000
1.000
0.030
0.000
-
N
[kg/kg]
0.000
0.000
0.000
0.040
0.000
-
O
[kg/kg]
0.000
0.000
0.000
0.080
0.000
-
H2O
[kg/kg]
0.000
0.000
0.000
0.020
0.000
-
CH4
[kg/kg]
-
-
-
-
-
1.000
Fuel
Carbon
Hydrogen
Sulfur
Coal
Oil
Gas
N
[kmol/kmol]
0.790
O
[kmol/kmol]
0.210
N
[kg/kg]
0.767
O
[kg/kg]
0.233
Oxidant
Air

63. Combustion
Stoichiometric Combustion
Flame Temperature
Hydrogen
[K]
2,525
2,583
2,640
2,689
2,757
2,818
2,879
2,942
Sulfur
[K]
1,972
2,045
2,118
2,191
2,267
2,343
2,421
2,501
Coal
[K]
2,484
2,551
2,618
2,686
2,756
2,827
2,899
2,972
Oil
[K]
2,484
2,551
2,616
2,683
2,751
2,820
2,891
2,963
Preheat Temperature
[K]
298
400
500
600
700
800
900
1,000
Combustion Products Stoichiometric Oxidant to Fuel Ratio and HHV
Stoichiometric
Oxidant to Fuel Ratio
[/]
11.444
34.333
4.292
10.487
14.649
17.167
HHV
[Btu/lbm]
14,094
60,997
3,982
14,162
20,660
21,563
Fuel
Carbon
Hydrogen
Sulfur
Coal
Oil
Gas
Gas
[K]
2,327
2,391
2,455
2,520
2,586
2,653
2,721
2,791
Carbon
[K]
2,460
2,531
2,602
2,674
2,747
2,822
2,898
2,976

64. Combustion Products Flame Temperature
0
1,000
2,000
3,000
298 400 500 600 700 800 900 1,000
FlameTemperature[K]
Carbon Hydrogen Sulfur Coal Oil Gas
Combustion
Fuel Inlet Temperature: 298 [K]
Oxidant Preheat Temperature for Stoichiometric Combustion Conditions

65. Combustion
298
[K]
2,460
2,361
2,262
2,163
400
[K]
2,531
2,433
2,334
2,235
500
[K]
2,602
2,503
2,405
2,306
600
[K]
2,674
2,575
2,477
2,378
700
[K]
2,747
2,649
2,551
2,452
800
[K]
2,822
2,724
2,626
2,527
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Preheat
Fuel: Carbon
900
[K]
2,898
2,800
2,702
2,604
1,000
[K]
2,976
2,878
2,780
2,682

66. Combustion
298
[K]
2,525
2,409
2,293
2,176
400
[K]
2,583
2,468
2,351
2,235
500
[K]
2,640
2,525
2,409
2,293
600
[K]
2,698
2,583
2,468
2,352
700
[K]
2,757
2,643
2,528
2,412
800
[K]
2,818
2,704
2,589
2,474
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Preheat
Fuel: Hydrogen
900
[K]
2,879
2,765
2,651
2,536
1,000
[K]
2,942
2,828
2,714
2,600

67. Combustion
298
[K]
1,972
1,895
1,818
1,741
400
[K]
2,045
1,969
1,892
1,815
500
[K]
2,118
2,041
1,965
1,888
600
[K]
2,191
2,115
2,039
1,963
700
[K]
2,267
2,191
2,115
2,039
800
[K]
2,343
2,268
2,192
2,116
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Preheat
Fuel: Sulfur
900
[K]
2,421
2,346
2,270
2,195
1,000
[K]
2,501
2,426
2,350
2,275

68. Combustion
298
[K]
2,484
2,381
2,278
2,174
400
[K]
2,551
2,449
2,346
2,243
500
[K]
2,618
2,516
2,413
2,310
600
[K]
2,686
2,584
2,482
2,379
700
[K]
2,756
2,654
2,552
2,449
800
[K]
2,827
2,725
2,623
2,521
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Preheat
Fuel: Coal
900
[K]
2,899
2,797
2,695
2,593
1,000
[K]
2,972
2,871
2,769
2,667

69. Combustion
298
[K]
2,484
2,379
2,274
2,167
400
[K]
2,551
2,446
2,340
2,235
500
[K]
2,616
2,512
2,406
2,301
600
[K]
2,683
2,578
2,474
2,368
700
[K]
2,751
2,647
2,542
2,437
800
[K]
2,820
2,716
2,612
2,507
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Preheat
Fuel: Oil
900
[K]
2,891
2,787
2,683
2,579
1,000
[K]
2,963
2,859
2,755
2,651

70. Combustion
298
[K]
2,327
2,236
2,145
2,053
400
[K]
2,391
2,301
2,210
2,118
500
[K]
2,455
2,365
2,274
2,182
600
[K]
2,520
2,429
2,339
2,248
700
[K]
2,586
2,496
2,405
2,315
800
[K]
2,653
2,563
2,473
2,383
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Preheat
Fuel: Gas
900
[K]
2,721
2,632
2,542
2,452
1,000
[K]
2,791
2,702
2,612
2,522

71. Combustion Products Flame Temperature
0
1,000
2,000
3,000
298 400 500 600 700 800 900 1,000
FlameTemperature[K]
85 90 95 100
Combustion
Fuel Inlet Temperature: 298 [K]
Oxidant Preheat Temperature for Stoichiometric Combustion Conditions
Fuel: Carbon
Combustion Efficiency [%]

72. Combustion Products Flame Temperature
0
1,000
2,000
3,000
298 400 500 600 700 800 900 1,000
FlameTemperature[K]
85 90 95 100
Combustion
Fuel Inlet Temperature: 298 [K]
Oxidant Preheat Temperature for Stoichiometric Combustion Conditions
Fuel: Hydrogen
Combustion Efficiency [%]

73. Combustion Products Flame Temperature
0
1,000
2,000
3,000
298 400 500 600 700 800 900 1,000
FlameTemperature[K]
85 90 95 100
Combustion
Fuel Inlet Temperature: 298 [K]
Oxidant Preheat Temperature for Stoichiometric Combustion Conditions
Fuel: Sulfur
Combustion Efficiency [%]

74. Combustion Products Flame Temperature
0
1,000
2,000
3,000
298 400 500 600 700 800 900 1,000
FlameTemperature[K]
85 90 95 100
Combustion
Fuel Inlet Temperature: 298 [K]
Oxidant Preheat Temperature for Stoichiometric Combustion Conditions
Fuel: Coal
Combustion Efficiency [%]

75. Combustion Products Flame Temperature
0
1,000
2,000
3,000
298 400 500 600 700 800 900 1,000
FlameTemperature[K]
85 90 95 100
Combustion
Fuel Inlet Temperature: 298 [K]
Oxidant Preheat Temperature for Stoichiometric Combustion Conditions
Fuel: Oil
Combustion Efficiency [%]

76. Combustion Products Flame Temperature
0
1,000
2,000
3,000
298 400 500 600 700 800 900 1,000
FlameTemperature[K]
85 90 95 100
Combustion
Fuel Inlet Temperature: 298 [K]
Oxidant Preheat Temperature for Stoichiometric Combustion Conditions
Fuel: Gas
Combustion Efficiency [%]

77. Combustion
Oxidant Composition
Fuel Composition
C
[kg/kg]
1.000
0.000
0.000
0.780
0.860
-
H
[kg/kg]
0.000
1.000
0.000
0.050
0.140
-
S
[kg/kg]
0.000
0.000
1.000
0.030
0.000
-
N
[kg/kg]
0.000
0.000
0.000
0.040
0.000
-
O
[kg/kg]
0.000
0.000
0.000
0.080
0.000
-
H2O
[kg/kg]
0.000
0.000
0.000
0.020
0.000
-
CH4
[kg/kg]
-
-
-
-
-
1.000
Fuel
Carbon
Hydrogen
Sulfur
Coal
Oil
Gas
N
[kmol/kmol]
0.790
O
[kmol/kmol]
0.210
N
[kg/kg]
0.767
O
[kg/kg]
0.233
Oxidant
Air

78. Combustion
Combustion Products Composition on Weight and Mole Basis
Combustion Products Flame Temperature and Oxidant to Fuel Ratio
Flame Temperature
[K]
2,460
1,506
1,145
952
831
748
Oxidant to Fuel Ratio
[/]
11.444
22.889
34.333
45.778
57.222
68.667
Stoichiometry
[/]
1
2
3
4
5
6
Fuel: Carbon
CO2
[kg/kg]
0.295
0.153
0.104
0.083
0.063
0.053
H2O
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
SO2
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kg/kg]
0.705
0.735
0.745
0.751
0.754
0.756
O2
[kg/kg]
0.000
0.112
0.151
0.171
0.183
0.191
CO2
[kmol/kmol]
0.210
0.105
0.070
0.053
0.042
0.035
Stoichiometry
[/]
1
2
3
4
5
6
SO2
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kmol/kmol]
0.790
0.790
0.790
0.790
0.790
0.790
H2O
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
O2
[kmol/kmol]
0.000
0.105
0.140
0.157
0.168
0.175

79. Combustion
1
[K]
2,460
2,361
2,262
2,163
2
[K]
1,506
1,450
1,395
1,339
3
[K]
1,145
1,106
1,066
1,027
4
[K]
952
922
891
860
5
[K]
831
806
781
755
6
[K]
748
726
705
683
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Stoichiometry
Fuel: Carbon

80. Combustion
Combustion Products Composition on Weight and Mole Basis
Flame Temperature
[K]
2,525
1,645
1,269
1,059
924
830
Oxidant to Fuel Ratio
[/]
34.333
68.667
103.000
137.333
171.667
206.000
Stoichiometry
[/]
1
2
3
4
5
6
Fuel: Hydrogen
CO2
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
H2O
[kg/kg]
0.255
0.129
0.087
0.065
0.052
0.043
SO2
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kg/kg]
0.745
0.756
0.760
0.761
0.763
0.763
O2
[kg/kg]
0.000
0.115
0.154
0.173
0.185
0.193
CO2
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
Stoichiometry
[/]
1
2
3
4
5
6
SO2
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kmol/kmol]
0.653
0.715
0.738
0.751
0.758
0.763
H2O
[kmol/kmol]
0.347
0.190
0.131
0.100
0.081
0.068
O2
[kmol/kmol]
0.000
0.095
0.131
0.150
0.161
0.169
Combustion Products Flame Temperature and Oxidant to Fuel Ratio

81. Combustion
1
[K]
2,525
2,409
2,293
2,176
2
[K]
1,645
1,574
1,502
1,430
3
[K]
1,269
1,217
1,164
1,111
4
[K]
1,059
1,017
976
934
5
[K]
924
890
855
820
6
[K]
830
800
771
741
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Stoichiometry
Fuel: Hydrogen

82. Combustion
Combustion Products Composition on Weight and Mole Basis
Flame Temperature
[K]
1,972
1,229
949
799
705
641
Oxidant to Fuel Ratio
[/]
4.292
8.583
12.875
17.167
21.458
25.750
Stoichiometry
[/]
1
2
3
4
5
6
Fuel: Sulfur
CO2
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
H2O
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
SO2
[kg/kg]
0.378
0.209
0.144
0.110
0.089
0.075
N2
[kg/kg]
0.622
0.687
0.712
0.725
0.733
0.738
O2
[kg/kg]
0.000
0.104
0.144
0.165
0.178
0.187
CO2
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
Stoichiometry
[/]
1
2
3
4
5
6
SO2
[kmol/kmol]
0.210
0.105
0.070
0.053
0.042
0.035
N2
[kmol/kmol]
0.790
0.790
0.790
0.790
0.790
0.790
H2O
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
O2
[kmol/kmol]
0.000
0.105
0.140
0.158
0.168
0.175
Combustion Products Flame Temperature and Oxidant to Fuel Ratio

83. Combustion
1
[K]
1,972
1,895
1,818
1,741
2
[K]
1,229
1,186
1,143
1,099
3
[K]
949
918
888
857
4
[K]
799
775
751
727
5
[K]
705
685
666
646
6
[K]
641
624
607
591
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Stoichiometry
Fuel: Sulfur

84. Combustion
Combustion Products Composition on Weight and Mole Basis
Fuel: Coal
CO2
[kg/kg]
0.249
0.130
0.088
0.067
0.053
0.045
H2O
[kg/kg]
0.041
0.021
0.014
0.011
0.009
0.007
SO2
[kg/kg]
0.005
0.003
0.002
0.001
0.001
0.001
N2
[kg/kg]
0.705
0.735
0.745
0.750
0.754
0.756
O2
[kg/kg]
0.000
0.111
0.151
0.171
0.183
0.191
CO2
[kmol/kmol]
0.170
0.087
0.059
0.044
0.035
0.030
Stoichiometry
[/]
1
2
3
4
5
6
SO2
[kmol/kmol]
0.002
0.001
0.001
0.001
0.001
0.000
N2
[kmol/kmol]
0.760
0.774
0.779
0.782
0.783
0.785
H2O
[kmol/kmol]
0.068
0.035
0.024
0.018
0.014
0.012
O2
[kmol/kmol]
0.000
0.103
0.138
0.156
0.166
0.174
Flame Temperature
[K]
2,484
1,544
1,178
981
856
769
Oxidant to Fuel Ratio
[/]
10.487
20.992
31.497
42.002
52.507
63.013
Stoichiometry
[/]
1
2
3
4
5
6
Combustion Products Flame Temperature and Oxidant to Fuel Ratio

85. Combustion
1
[K]
2,484
2,381
2,278
2,174
2
[K]
1,544
1,486
1,427
1,367
3
[K]
1,178
1,136
1,094
1,051
4
[K]
981
948
915
881
5
[K]
856
829
801
774
6
[K]
769
746
723
699
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Stoichiometry
Fuel: Coal

86. Combustion
Combustion Products Composition on Weight and Mole Basis
Flame Temperature
[K]
2,484
1,555
1,187
989
863
776
Oxidant to Fuel Ratio
[/]
14.694
29.298
43.947
58.596
73.244
87.893
Stoichiometry
[/]
1
2
3
4
5
6
Fuel: Oil
CO2
[kg/kg]
0.202
0.104
0.070
0.053
0.042
0.035
H2O
[kg/kg]
0.080
0.042
0.028
0.021
0.017
0.014
SO2
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kg/kg]
0.718
0.742
0.750
0.754
0.757
0.758
O2
[kg/kg]
0.000
0.113
0.152
0.172
0.184
0.192
CO2
[kmol/kmol]
0.132
0.068
0.046
0.035
0.028
0.023
Stoichiometry
[/]
1
2
3
4
5
6
SO2
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kmol/kmol]
0.739
0.764
0.772
0.777
0.779
0.781
H2O
[kmol/kmol]
0.129
0.067
0.045
0.034
0.027
0.023
O2
[kmol/kmol]
0.000
0.102
0.137
0.155
0.166
0.173
Combustion Products Flame Temperature and Oxidant to Fuel Ratio

87. Combustion
1
[K]
2,484
2,379
2,274
2,167
2
[K]
1,555
1,494
1,433
1,371
3
[K]
1,187
1,144
1,100
1,056
4
[K]
989
954
920
885
5
[K]
863
834
806
777
6
[K]
776
751
727
702
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Stoichiometry
Fuel: Oil

88. Combustion
Combustion Products Composition on Weight and Mole Basis
Flame Temperature
[K]
2,327
1,480
1,137
951
832
750
Oxidant to Fuel Ratio
[/]
17.167
34.333
51.500
68.667
85.833
103.000
Stoichiometry
[/]
1
2
3
4
5
6
Fuel: Gas
CO2
[kg/kg]
0.151
0.078
0.052
0.039
0.032
0.026
H2O
[kg/kg]
0.124
0.064
0.043
0.032
0.026
0.022
SO2
[kg/kg]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kg/kg]
0.725
0.745
0.752
0.756
0.758
0.760
O2
[kg/kg]
0.000
0.113
0.152
0.172
0.184
0.192
CO2
[kmol/kmol]
0.095
0.050
0.034
0.026
0.021
0.017
Stoichiometry
[/]
1
2
3
4
5
6
SO2
[kmol/kmol]
0.000
0.000
0.000
0.000
0.000
0.000
N2
[kmol/kmol]
0.715
0.751
0.763
0.770
0.774
0.776
H2O
[kmol/kmol]
0.190
0.100
0.068
0.051
0.041
0.034
O2
[kmol/kmol]
0.000
0.100
0.135
0.153
0.165
0.172
Combustion Products Flame Temperature and Oxidant to Fuel Ratio

89. Combustion
1
[K]
2,327
2,236
2,145
2,053
2
[K]
1,480
1,426
1,372
1,317
3
[K]
1,137
1,099
1,060
1,020
4
[K]
951
920
889
859
5
[K]
832
807
781
756
6
[K]
750
728
706
685
Combustion Efficiency
[/]
1.00
0.95
0.90
0.85
Combustion Products Ideal vs Real Flame Temperature as a Function of Stoichiometry
Fuel: Gas

90. Combustion Products -- Weight Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kg/kg]
1 2 3 4 5 6
Combustion
Stoichiometry [/]
Fuel: Carbon
Fuel and Oxidant Inlet Temperature: 298 [K]

91. Combustion Products -- Mole Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kmol/kmol]
1 2 3 4 5 6
Combustion
Stoichiometry [/]
Fuel: Carbon
Fuel and Oxidant Inlet Temperature: 298 [K]

92. Combustion Products -- Weight Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kg/kg]
1 2 3 4 5 6
Combustion
Fuel: Hydrogen
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

93. Combustion Products -- Mole Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kmol/kmol]
1 2 3 4 5 6
Combustion
Fuel: Hydrogen
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

94. Combustion Products -- Weight Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kg/kg]
1 2 3 4 5 6
Combustion
Fuel: Sulfur
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

95. Combustion Products -- Mole Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kmol/kmol]
1 2 3 4 5 6
Combustion
Fuel: Sulfur
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

96. Combustion Products -- Weight Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kg/kg]
1 2 3 4 5 6
Combustion
Fuel: Coal
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

97. Combustion Products -- Mole Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kmol/kmol]
1 2 3 4 5 6
Combustion
Fuel: Coal
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

98. Combustion Products -- Weight Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kg/kg]
1 2 3 4 5 6
Combustion
Fuel: Oil
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

99. Combustion Products -- Mole Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kmol/kmol]
1 2 3 4 5 6
Combustion
Fuel: Oil
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

100. Combustion Products -- Weight Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kg/kg]
1 2 3 4 5 6
Combustion
Fuel: Gas
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

101. Combustion Products -- Mole Basis
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
CO2 H2O SO2 N2 O2
CombustionProducts[kmol/kmol]
1 2 3 4 5 6
Combustion
Fuel: Gas
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

102. Combustion Products Flame Temperature
600
1,100
1,600
2,100
2,600
1 2 3 4 5 6
FlameTemperature[K]
Carbon Hydrogen Sulfur Coal Oil Gas
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

103. Combustion Products Flame Temperature
500
1,000
1,500
2,000
2,500
3,000
1 2 3 4 5 6
FlameTemperature[K]
85 90 95 100
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Fuel: Carbon
Stoichiometry [/]
Combustion Efficiency [%]

104. Combustion Products Flame Temperature
500
1,000
1,500
2,000
2,500
3,000
1 2 3 4 5 6
FlameTemperature[K]
85 90 95 100
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Fuel: Hydrogen
Stoichiometry [/]
Combustion Efficiency [%]

105. Combustion Products Flame Temperature
500
1,000
1,500
2,000
2,500
3,000
1 2 3 4 5 6
FlameTemperature[K]
85 90 95 100
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Fuel: Sulfur
Stoichiometry [/]
Combustion Efficiency [%]

106. Combustion Products Flame Temperature
500
1,000
1,500
2,000
2,500
3,000
1 2 3 4 5 6
FlameTemperature[K]
85 90 95 100
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Fuel: Coal
Stoichiometry [/]
Combustion Efficiency [%]

107. Combustion Products Flame Temperature
500
1,000
1,500
2,000
2,500
3,000
1 2 3 4 5 6
FlameTemperature[K]
85 90 95 100
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Fuel: Oil
Stoichiometry [/]
Combustion Efficiency [%]

108. Combustion Products Flame Temperature
500
1,000
1,500
2,000
2,500
3,000
1 2 3 4 5 6
FlameTemperature[K]
85 90 95 100
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Combustion Efficiency [%]
Fuel: Gas
Stoichiometry [/]

109. Combustion Oxidant to Fuel Ratio
0
40
80
120
160
200
240
1 2 3 4 5 6
OxidanttoFuelRatio[/]
Carbon Hydrogen Sulfur Coal Oil Gas
Combustion
Fuel and Oxidant Inlet Temperature: 298 [K]
Stoichiometry [/]

110. Expansion Schematic Layout
Working Fluid In
Working Fluid Out
Turbine
1
2
Expansion

111. Expansion T - s Diagram
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Expansion
1
2s
2

112. Expansion Specific Power Output
400
500
600
700
800
900
5 10 15
Expansion Ratio (P1/P2) [/]
ExpansionSpecificPowerOutput[kJ/kg]
85 90 95 100
Working Fluid: Air
Turbine Inlet Temperature: 1,500 [K] -- Ambient Pressure: 1 [atm]
Expansion
Isentropic Expansion Efficiency [%]

113. Expansion Power Output
0
40
80
120
160
50 100 150
Working Fluid Mass Flow Rate [kg/s]
ExpansionPowerOutput[MW]
85 90 95 100
Working Fluid: Air
Turbine Inlet Temperature: 1,500 [K] -- Expansion Ratio (P1/P2): 15 [/]
Expansion
Isentropic Expansion Efficiency [%]

114. Power Cycle Components/Processes
Conclusions
The compression specific power input increases with an increase in the compression
ratio values for a fixed compression inlet temperature. As the working fluid mass flow
rate increases for the fixed compression ratio and compression inlet temperature
values, the compression power input requirements increase too. As the isentropic
compression efficiency decreases, the compression power input increases.
Hydrogen as the fuel has the highest flame temperature, requires the most mass
amount of oxidant/air in order to have complete combustion per unit mass amount of
fuel and has the largest fuel higher heating value. As the combustion efficiency
decreases, the combustion products flame temperature decreases.
When hydrogen reacts with oxidant/air, there is no CO2 present in the combustion
products.
The expansion specific power output increases with an increase in the expansion ratio
values for a fixed expansion inlet temperature. As the working fluid mass flow rate
increases for the fixed expansion ratio and expansion inlet temperature values, the
expansion power output values increase too. As the isentropic expansion efficiency
decreases, the expansion power output decreases.

115. Sonic Velocity
vsonic = (χ RT)1/2 [m/s]
Mach Number
M = v/vsonic [/]
Compressible Flow Engineering Equations

116. Isentropic Flow
Tt/Ts = (1 + M2(χ - 1)/2) [/]
pt/p = (1 + M2(χ - 1)/2)χ/(χ-1) [/]
ht = (hs + v2/2) [kJ/kg]
Tt = (Ts + v2/(2cp)) [K]
n = (T1 - T2)/(T1 - T2s) [/]
d = (T2s - T 1)/(T2 - T1) [/]
Thrust = vm + (p - pa)A [N]
Compressible Flow Engineering Equations

117. Nozzle Schematic Layout
Working Fluid In Working Fluid Out
Nozzle
1 2
Nozzle

118. Nozzle T - s Diagram
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Nozzle
1
2s
2

119. Nozzle Performance
0.2
0.4
0.6
0.8
1.0
400 500 600
Velocity [m/s]
MachNumber[/]
85 90 95 100
Nozzle
Nozzle Inlet Stagnation Conditions -- Temperature: 1,500 [K] and Pressure: 10 [atm]
Isentropic Nozzle Efficiency [%]

120. Nozzle Performance
1.00
1.05
1.10
1.15
1.20
400 500 600
Velocity [m/s]
Tstagnation/Tstatic[/]
85 90 95 100
Nozzle
Nozzle Inlet Stagnation Conditions -- Temperature: 1,500 [K] and Pressure: 10 [atm]
Isentropic Nozzle Efficiency [%]

121. Nozzle Performance
1.20
1.30
1.40
1.50
1.60
400 500 600
Velocity [m/s]
Pstagnation/Pstatic[/]
85 90 95 100
Nozzle
Nozzle Inlet Stagnation Conditions -- Temperature: 1,500 [K] and Pressure: 10 [atm]
Isentropic Nozzle Efficiency [%]

122. Diffuser Schematic Layout
Working Fluid In Working Fluid Out
Diffuser
1 2
Diffuser

123. Diffuser T - s Diagram
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Diffuser
2s
1
2

124. Diffuser Performance
0.2
0.4
0.6
0.8
1.0
100 200 300
Velocity [m/s]
MachNumber[/]
85 90 95 100
Diffuser
Diffuser Inlet Static Conditions -- Temperature: 298 [K] and Pressure: 1 [atm]
Isentropic Diffuser Efficiency [%]

125. Diffuser Performance
1.00
1.05
1.10
1.15
1.20
100 200 300
Velocity [m/s]
Tstagnation/Tstatic[/]
85 90 95 100
Diffuser
Isentropic Diffuser Efficiency [%]
Diffuser Inlet Static Conditions -- Temperature: 298 [K] and Pressure: 1 [atm]

126. Diffuser Performance
1.20
1.30
1.40
1.50
1.60
100 200 300
Velocity [m/s]
Pstagnation/Pstatic[/]
85 90 95 100
Diffuser
Isentropic Diffuser Efficiency [%]
Diffuser Inlet Static Conditions -- Temperature: 298 [K] and Pressure: 1 [atm]

127. Thrust Schematic Layout
Working Fluid Out
Nozzle
21
Working Fluid at Still
Thrust

128. Thrust T - s Diagram
Temperature--T[K]
Entropy -- s [kJ/kg*K]
Thrust
1
2s
2

129. Nozzle Performance
0.6
0.7
0.8
0.9
1.0
900 1,200 1,500
Nozzle Inlet Stagnation Temperature [K]
MachNumber[/]
85 90 95 100
Thrust
Isentropic Nozzle Efficiency [%]
Nozzle Inlet Stagnation Conditions -- Pressure: 10 [atm]
Nozzle Outlet Static Conditions -- Mach Number: 0.85 [/]

130. Nozzle Performance
1.00
1.05
1.10
1.15
1.20
900 1,200 1,500
Nozzle Inlet Stagnation Temperature [K]
Tstagnation/Tstatic[/]
85 90 95 100
Thrust
Isentropic Nozzle Efficiency [%]
Nozzle Inlet Stagnation Conditions -- Pressure: 10 [atm]
Nozzle Outlet Static Conditions -- Mach Number: 0.85 [/]

131. Nozzle Performance
1.40
1.50
1.60
1.70
1.80
900 1,200 1,500
Nozzle Inlet Stagnation Temperature [K]
Pstagnation/Pstatic[/]
85 90 95 100
Thrust
Nozzle Inlet Stagnation Conditions -- Pressure: 10 [atm]
Isentropic Nozzle Efficiency [%]
Nozzle Outlet Static Conditions -- Mach Number: 0.85 [/]

132. Thrust
800
900
1,000
1,100
1,200
900 1,200 1,500
Nozzle Inlet Stagnation Temperature [K]
Thrust[N]
85 90 95 100
Working Fluid Mass Flow Rate: 1 [kg/s]
Thrust
Nozzle Outlet Static Conditions -- Mach Number: 0.85 [/]
Nozzle Inlet Stagnation Pressure: 10 [atm] and Ambient Conditions Pressure: 1 [atm]
Isentropic Nozzle Efficiency [%]

133. Compressible Flow Conclusions
Nozzle stagnation over static temperature and pressure ratio values increase with an
increase in the velocity (Mach Number).
Diffuser stagnation over static temperature and pressure ratio values increase with an
increase in the velocity (Mach Number).
Thrust increases with an increase in the inlet stagnation temperature.
As the nozzle and diffuser efficiency values decrease, the nozzle, diffuser and thrust
performance decreases.