Time-resolved temperature profile measurements in the exhaust of a single sector gas turbine combustor at realistic operating conditions

被引:9
作者
Greifenstein, M. [1 ]
Heinze, J. [2 ]
Willert, C. [2 ]
Voigt, L. [2 ]
Zedda, M. [3 ]
Richter, C. [4 ]
Dreizler, A. [1 ]
机构
[1] Tech Univ Darmstadt, Inst React Flows & Diagnost, Otto Berndt Str 3, D-64287 Darmstadt, Germany
[2] Deutsch Zentrum Luft & Raumfahrt DLR, Inst Prop Technol, D-51170 Cologne, Germany
[3] Rolls Royce Plc, Combust Aerothermal Methods, POB 31, Derby DE24 8BJ, England
[4] Rolls Royce Deutschland Ltd & Co KG, Aeroacoust & Noise, Syst Design, Eschenweg 11, D-15827 Dahlewitz, Germany
基金
欧盟地平线“2020”;
关键词
LASER-INDUCED FLUORESCENCE; THERMOMETRY; PHASE;
D O I
10.1007/s00348-020-03011-8
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
Records of the time-varying temperature profile at flight relevant operating conditions are acquired at the exit of a combustion chamber fitted with a staged, lean-burn fuel injector using high-speed laser induced fluorescence (LIF) at a sample rate of 10 kHz. Temperatures are estimated from the concentration dependent fluorescence of the hydroxyl (OH) radical under the assumption of local equilibrium. Beyond the time-series analysis, the acquired data is correlated with simultaneously acquired OH chemiluminescence sampled in the primary zone near the fuel injector. These analyses reveal a strong influence from the precessing vortex core, originating in the primary zone, on oscillations in the temperature profiles measured at the exit of the combustor. [GRAPHICS] .
引用
收藏
页数:12
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