Bearing Failure Investigation of Turbomachinery Test Rig

This paper presents the investigation of bearing failure in a compressor test rig which has been satisfactorily in operation. Two pair of single row angular contact ball bearings, each pair in tandem, and the pairs in turn in back to back support the rotor shaft to meet compressor thrust and to provide moderate stiffness for smooth operation. Since being experimental rig, it is reassembled several times involving bearing replacements on each occasion. Recently one bearing on one side pair is found severely damaged and the other bearing of the pair with minor damage. The bearing with minor damage supported the rotor and this evaded the initial diagnostics until the time of severe damage. Initial investigation revealed that the primary cause of failure is washed off by the secondary failure. A thorough, systematic investigation with the help of fishbone approach is carried in order to find out the root cause of the failure and also to decide on new rig. This investigation revealed lack of preload as the major cause and bearing seat clearance as minor problem. New procedure is adopted to ensure proper preload and the rig is back in operation

Development of a High Pressure Ratio Axial Fan Stage with Non-metallic Rotor Blads

This project proposal is submitted to GATET at GTf :E for funding. The research programme envisages the Development of a high Pressure Ratio Axial Fan Stage with Non-metallic Rotor Blades for Small Gas Turbine Engine". The novelty of the Project is to demonstrate a 2: 1 pressure ratio in single stage fan with tip diameter of 316mm, rotor tip speed of 470 m/s and rotational speed of 28400 rpm

Design, Fabrication and Testing of Pressure Adaptors and Temperature Sensors for an Aero Engine Health Monitoring

Engine Health Monitoring (EHM) systems are becoming essential parts of modern aircraft engines to enhance safe and long operation and to reduce down time. Activities initiated to develop EHM for a typical aero engine under NPMASS sponsored project. It is planned to acquire detailed gas path data to evaluate engine performance parameters more accurately. This requires additional sensors to be incorporated in the engine gas path along with the available sensors already mounted by the manufacturer. Consequently, an assignment has been taken under EHM program to mount additional sensors in a typical aero engine with active participation from HAL / RCMA, Koraput. The design, fabrication, assembly and testing of several pressure sensing adaptors and temperature sensors have been discussed in detail in this report. The mechanical design of adaptors / sensors has been made to meet the requirements of high temperature and vibration environment during all the ratings of the engine test. The preliminary trial test for the fabricated sensor components has been carried out in the engine test bed. Satisfactory results of the components have been observed during trial tests