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Abstract The mismatching phenomenon between compressor and combustor in gas turbines may cause inlet distortion at combustor entrance, which has an influence on combustion performances. An experimental investigation was carried out in the prevent study to reveal the relationship between inlet distortion and combustion performances. During the experimental work, inlet distortions were introduced by locating orifice plates at the combustor inlet, including mid-peak, upper-biased peak, lower-biased peak. The exhaust gas were measured by the outlet thermal-couple and gas analyzer. Results show that the distortion form and operating conditions have a minor impact on combustion efficiency, whereas they significantly affect the total pressure loss coefficient and the outlet temperature distribution factor (OTDF). In particular, under conditions of higher distortion, the total pressure loss coefficient increases significantly. When the inlet non-uniformity increases from 4.15% to 51.37% (upper-biased peak), the total pressure loss coefficient increases by 2.65% (a 63% increase compared to the previous value), and the OTDF increases by 13.3% (a 67.5% increase compared to the previous value). Additionally, the impact of the upper-biased peak distortion on OTDF is greater than that of the lower-biased peak distortion.
Luo et al. (Mon,) studied this question.