DESAIN DAN ANALISIS DIFFUSER PADA MIKRO TURBOJET

• Main Author: Vince Sembiring - Nim: 13612022 , Andry
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/21081
• Institution: Institut Teknologi Bandung

One major change of military strategy is UAV will play a lot more portion in all military branches than before. UAVs are unmanned flying objects that have the characteristics of a manned flying object in general, the main advantages of using a pilot UAV are not flying with them so they are safer and have better flying resistance. In some experimental UAVs, micro turbojets are used which, according to the theory, provide the right thrust for UAVs Work on the final task is done by creating a diffuser model of the turbojet that will be installed on the aircraft. Diffuser to be used must meet the aspect of good airflow. Good airflow is characterized by the lack of separation and slight airflow turbulence. Turbulence is the occurrence of marked flow damage in the fluid flow (air) from the laminar air layer to the turbulent air layer. Good airflow produces good flow performance too. In the radial bar, a flow angle of 30 degrees is used. The selection of a minimum flow angle of 30 degrees is the selected angle after viewing stable flow conditions. The angle is obtained from the results of numerical research through the CFD program is ANSYS. These airflows are further required as combustion chamber air, so that air mixed with the fuel must have high pressure and low flow rate. The goal is for the burning process to take place with a stable. This diffuser allows fluid flowing into the combustion chamber to have high pressure and low speed / flow rate thus optimizing combustion process in the combustion chamber. <br /> <br /> <br /> <br /> <br />