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This paper deals with effect of evaporative inlet air cooling on exergy and emission in basic gas turbine cycle. Inlet air cooled gas turbine based power plants are operational in various parts of the world. The article is an attempt to analyze thermodynamic and emission performance to these cycles. Rational efficiency of gas turbine for cooled inlet air at lower relative humidity is higher; also the exergy destruction in combustor is higher among all other components. For a fixed value of equivalence ratio, residence time, turbine-rotor-inlet temperature and two varying relative humidity effect of various values of compressor ratio on primary-zone-temperature, NOx, CO and UHC emission has been analyzed. It has been observed that the primary-zone-temperature and mass of NOX emission increases with increase in compressor pressure ratio whereas mass of CO and UHC emission decreases with increase in compressor pressure ratio.

In modern turboprop engines, reduction in emission and fuel consumption is the primary goals during the development of gas turbine aero engines. In this paper, a concept has been proposed for hybridizing the air blade cooled turboprop engines by integrating it with a fuel cell. The proposed study focuses on thermodynamic analysis of a turboprop engine integrated to a solid oxide fuel cell (SOFC) system. A solid oxide fuel cell is the perfect candidate for utilizing waste heat available at turboprop engine exhaust, through recuperation process. Integration of SOFC is ultimately leads to enhancement the overall performance of the turboprop-SOFC hybrid system. Power generated by the SOFC system can be utilized by the aircraft and in can complement the auxillary-power-unit (APU) and may even supplement it. On the basis of 1st and 2nd law of thermodynamic modeling analysis of a turboprop-SOFC system has been presented in this article.