مهندس سید محمد واعظی

In recent centuries energy has become of great importance due to the shortage of energy resources and energy losses. Efficient use of energy and minimizing energy waste has become one of the largest research purposes and achieving this goal has provided the field of production of the devices. In this research, the construction of a high-temperature heat pipe with mercury as the working fluid as well as CFD simulation of the heat pipe is investigated and the obtained results are presented. The factors affecting the heat transfer of the heat pipe, including the evaporator and condenser internal heat transfer coefficients and the thermal conductivity coefficient are empirically and numerically investigated and the results are reported as the diagram. The results show that the heat pipe in the heat flux of 278 watts has an efficiency of 0.89 and has the lowest thermal resistance (R=1.3 °C/W) against the heat transfer, which has a better performance than the lower input heat fluxes. The heat pipe built in temperature range close to the design conditions delivers more acceptable performance.

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.