| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 101 === The purpose of this research is to inject hydrogen into a turbine engine which consumes liquid fuel (JP-8) as major fuel. The turbine engine is composed with a turbocharger (TD-08) and a combustor which is designed in laboratory. In all stations there are 5 thermocouples and 4 pressure sensors installed. The exhaust extractor combines with gas analyzer which is installed outside the turbine exit. Amount of hydrogen (7.67L/min~71.8L/min)less than 6% based on total heat of fuel are injected into the combustor in order to examinate the influence of combustion performance by monition parameters like temperature, pressure, RPM, and its exhaust(CO, HC and NOx), etc.
From results of this research, it was found out that with hydrogen injection the high temperature area moves upstream in the combustor which can verify hydrogen enhancing combustion process. Furthermore, its trends of CO, HC, NOx concentration can be expected downward with hydrogen injected into the turbine engine. There is 56% decrease of CO,78% decrease of HC and 44% reduction of NOx. In summary, hydrogen injection does enhance combustion performance in micro turbine engine even with only 6% in total heat addition.
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