PENGUJIAN RUANG BAKAR REVERSE-ANNULAR DENGAN BAHAN BAKAR DIESEL

• Main Author: Prayogo, Herdianto
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/45591
• Institution: Institut Teknologi Bandung

Turbine gases are turbomachinery that takes energy from the combustion process. A compressor increasse pressure at upstream. After combustion process at downstream the turbine take energy from the combustion gas. The combustion process occurs at the combustion chamber which is between the turbine and compressor. The focus of this paper is the combustion chamber. The combustion chamber is part of turbin gas that brings air and fuel together. The meeting of the two fluids will be conditioned with enough heat for the combustion reaction to occur. Combustion process occured in the combustion chamber are controlled in such a way that the combustion process does not continue to the turbine. The combustion chamber is also designed to provide uniform heat distribution. Another parameter other than those mentioned which quite crucial is the ability to burn fuel as much as possible. The combustion chamber is usually divided into 3 zones. The first zone is when fuel is mixed with air and burned. Ideally combustion only takes place in this primary zone. In the next zone, a secondary zone can be added which functions to burn the remnants of fuel and finish the combustion process. In the next zone or dilution zone hot air mixed with cold air.It will reduce the temperature and make it uniform. One method to determine the performance of the combustion chamber is by testing. The heat distribution from the combustion chamber can be determined by directly measuring the exit temperature of the combustion chamber and determined by the value of the pattern factor. The efficiency of the combustion chamber is known by measuring the fuel entering the system and comparing it with the enthalpy increase in the fluid coming out of the combustion chamber. Besides that, it can also be seen visually whether or not there is a fire coming out of the combustion chamber. Tests will be conducted on various air and fuel ratios or fuel to air ratio. These results will determine whether or not the combustion chamber. The fuel used in the test this time is Pertamina Dex. Pertamina dex is Pertamina's fuel which is pretty much common on the market so it is easy to get.. In addition, Pertamina dex has a similar character to kerosene and jetA fuel. Many small turbo jets that are designed can use jet A fuel and diesel for example on AMT and Swiwin turbojet brands. Although turbo jets have a different purpose of generating thrust, they both use the Brayton cycle. From the results of the comparison, it was decided the use of Pertamina Dex could replace jet A fuel for use in turbin gase engines. The combustion chamber which will be tested is the result of optimization of the combustion chamber of previous research. The optimized combustion chamber has an annular reverese configuration with a diameter of 167 mm and a length of 265 mm. Based on the optimization results using a genetic algorithm the holes in the primary zone are the smallest and the holes in the cooling zone have a large diameter. In general, the design in the combustion chamber of the primary section has large holes and dilution has a small diameter. In the dilution section, a large diameter will provide good penetration into the center of the combustion chamber. Good penetration will make the middle of the hot air cooler. Combustion chamber with an unusual hole diameter needs to be tested for validation of the optimization results