Al-Qadisiyah Journal for Engineering Sciences

Abstract The gas turbine engines are occupied an important sector in the energy production and aviation industry and this important increase day after day for their features. One of the most important parameters that limit the gas turbine engine power output is the turbine inlet temperature. The higher is the turbine inlet temperature, the higher is the power output or thrust but this increases of risks of blade thermal failure due to metallurgical limits. Thus the need for a good and efficient process of blade cooling can lead to the best compromise between a powerful engine and safe operation. There are two major methods: film or external cooling and internal cooling inside the blade itself. . In the past number of years there has been considerable progress in turbine cooling research and this paper is limited to review a few selected publications to reflect recent development in turbine blade film cooling. The maximum drop in the surface temperature of the gas turbine blade and associated thermal stress – due to incorporating cooling systems- were 735 ˚C, 1217 N/mm² respectively.

Abstract The use of gas turbine is increasing day by day for producing electricity and for various industrial applications. In this work a new approach of study for the effect of different cycle arrangements on the performance of simple gas turbine has been investigated. The new cycle arrangements include: reheat with heat exchanger, reheat with water injection, heat exchanger with water injection and reheat together with heat exchanger and water injection. All these arrangements are compared to the performance of gas turbine cycle with no modifications. A Matlab code was written to calculate the combustion characteristics and major performance parameters such as net work, fuel/air ratio, specific fuel consumption, and thermal efficiency ….etc. It’s observed that using reheat in addition to heat exchanger with water injection gives higher thermal efficiency, maximum increment was 28.6% in compare with normal basic cycle and lower fuel consumption, maximum reduction was 22.2 in compare with normal basic cycle.

Abstract In this research, we study the effect of the some parameters (gas turbine speed, power turbine speed, mass flow rate of air, mass flow rate of fuel, compression ratio, air to fuel ratio and inlet compressor temperature) on the overall system efficiency, alternator efficiency and the overall heat efficiency of the two shaft gas turbine system, the working fluid was propane. Firstly we checked the experimental results by plotted the (T-S diagram) between the experimental and analytical solution and then we study the effect of the above parameters on the overall system efficiencies. Also we checked the effect of the inlet compressor temperature on the overall gas turbine performance .From these results, we can notes the increasing of the compression ratio and the power turbine speed will increase the overall efficiency, overall heat efficiency and decreasing the alternator efficiency, at the same time is increase the gas turbine efficiency