1.    Thermoacoustic characterization of Rijke tube device: experimental approach

Period                        : July 2004 to July 2005

Role                           : Post graduate student

Centre                       : Indian Institute of Technology, Bombay

Description:  Funded by the Defense Research and Development Organization (DRDO), the current research work focuses on the problem of thermoacoustic instabilities that are presently observed in recent designs of gas turbine systems. The research work primarily deals with the system identification of the dynamics, and understanding the effects of geometric variables, vorticity and heat transfer on thermoacoustic instabilities. The final goal is to develop experimentally based, yet physically correlated, models. These models will be useful to conduct linear stability analysis of the system. This research effort will also detail the process and techniques for dynamic characterization of a Rijke tube like device.

Responsible for designing and specifying a state of the art, experimental facility to study the thermo-acoustic instabilities. Various Rijke tube geometries can test in this setup.

2.    Enhancement of internal convective cooling in gas turbine blade passages (Kaveri Engine program)

Period                        : July 2002 to July 2003

Role                           : Research Fellow

Centre                       : National Aerospace Laboratories, Bangalore

Description:  Funded by Gas Turbine Research Establishment the project aimed at achieving better cooling of the high-pressure gas turbine blades of the newly developing Kaveri aircraft engine. The research primarily included experimental study of the geometries of the cooling passages inside the turbine blades intended for the convective cooling. The emphasis was on optimizing the cooling passages to avoid the existing hot spots, achieve better convective cooling, and hence high TET.

3.   Worked as a Graduate Trainee in ISRO, Liquid Propulsion Systems centre, Trivandrum from June 2001 to June2002.

         During this period, gained knowledge on the development, working and integration of the cryogenic (liquid hydrogen and liquid oxygen) rocket engine used in the maiden flight of GSLV. Also had the experience of working with eminent scientists who were developing the nation’s indigenous high performance (20 ton) cryogenic rocket engine (Mark III).