TABLE I Gas Temperature Distribution at Combustor Outlet
t I | adiabatic flame temp. |
measured aver- age temp., Tav |
measured max. temp., Tmax |
pattern factor |
nozzle A | 0.653 | 0.568 | 0.624 | 0.154 |
0.788 | 0.696 | 0.782 | 0.177 | |
0.903 | 0.819 | 0.982 | 0.266 | |
nozzle B | 0.644 | 0.547 | 0.594 | 0.138 |
0.776 | 0.679 | 0.765 | 0.182 | |
0.953 | 0.857 | 0.922 | 0.139 | |
1.026 | 0.926 | 1.026 | 0.140 |
Temperatures are normalized by 1700°C, pattern factor = (Tmax - Tav) / (Tav - inlet temp.). |
FIGURE 1 A Diagram of a Hydrogen Combustion Turbine
FIGURE 2 Test Apparatus and Combustor
FIGURE 3 Flow Chart of Continuous Gas Analysis System
FIGURE 4 Combustor Liner Temperatures
FIGURE 5 Residual Reactant Concentrations
FIGURE 6 Response Time of the Gas Analysis System
(Test Condition: Equivalence Ratio, 0.94 -> 0.96)