Performance and Emission Analysis of Combustion Chamber of a Turboprop Engine at Different Operation Regimes

Performance analysis of jet engines in various environmental conditions is important and is the first step in the design of such engines. In this paper, the performance of a typical turboprop engine was modeled in the commercial software GasTurb10 and the obtained results are validated at three flight regimes take off, military and 100% normal using engine test results. Performance analysis of combustion chamber was essential for estimating its exhaust gas temperature, which has influence on the lifetime and durability of engine hot section. In this study, one-dimensional performance analysis of a turboprop engine combustion chamber was carried out applying semi-experimental correlations. For this, a computer program called CLAD1 was developed in MATLAB. The results obtained for various engine operation regimes were compared with reliable experimental results. showing good agreements. The maximum relative error was 3.92% for military regime. Finally, the gas temperature distribution and emission of pollutants in different operation regimes were calculated and compared. The amount of NOx emission was maximum at take off flight regime, whereas the emission of pollutants CO and UHC have their highest values at 100% normal regime.