Failure Analysis of TJ-24 Turbojet Through Literature and Experimental Study

• Main Author: RIZKY LAKSANA (nim : 13114056), AKBAR
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/25266
• Institution: Institut Teknologi Bandung

<p align="justify"> The ability to develop micro turbojet is important for a country, especially Indonesia, because of its wide range application and crucial role. In ITB Mechanical Engineering Department, a micro turbojet with 24 Newton thrust specification was being developed under the name of TJ-24 from 2006 until now. Until now, TJ-24 has not yet able to reach idle operation and generate thrust force. TJ-24’s condition in the beginning of this project was unable to operate due to damage to the fuel pipe, NGV, and turbine components in previous research that generated 0.981 N thrust at 13,000 rpm. <br /> <br /> Reparation and replacement on the components stated above the were done to restore TJ-24’s conditions back to operable conditions and to conduct further testing. Testing is intended to measure compressor outlet pressure, compressor outlet temperature, turbine inlet temperature, turbine outlet temperature, fuel flow, also rotation and thrust force. <br /> <br /> Testing results shows that the maximum temperature reached was only 330 oC, the flame position was downstream of combustion chamber, compressor could not deliver pressure rise, and fuel flow only reached 23-28 g/min. Rotation speed only reached 5,400 rpm and no thrust were generated. Testing results yields a failure cause; diffusor is not optimal, combustion chamber design and geometry is not optimal, casing deformation, and absence of lubrication. <br /> <p align="justify">