Page 99 - Advanced Gas Turbine Cycles
P. 99
0.35
3
s
L 0.3
I-
v)
3
3 0.25
+r=20
+r=30
z 0.2
0 +t=35
I- +r=40
+T=45
3 0.15
LL -0-r=50
I ._..._ CHAPTER 4 ASSUMPTION
3
2 0.1
L
I-
Z
5 0.05
0
0
0
0
1200 1400 1600 1800 2000 2200
COMBUSTION TEMPERATURE - O C
Fig. 5.1. Calculated coolant air fractions for single step cooling (of nozzle guide vanes), as a function of combustion temperature with pressure ratio as a parameter.
