After graduating from Aerospace Engineering in Middle East Technical University (METU) in 2002, Erinç Erdem started working for Roketsan Missile Industries, Inc. as a propulsion engineer, focusing on internal aerodynamics of solid rocket motors. In 2005, Dr. Erdem obtained his research M.Sc. from von Karman Institute for Fluid Dynamics (VKI) on numerical and experimental investigation of internal flows inside a simplified Ariane 5 rocket motor geometry with slag accumulation.

In 2006, he obtained his M.Sc. from Mechanical Engineering in METU on a subject called numerical investigation of secondary gas injection systems for thrust vectoring. In 2011, he obtained a Ph.D. from the University of Manchester on active flow control studies at Mach 5 involving detailed wind tunnel measurements with various measurement techniques and complementary computational effort. Afterwards he carried on pursuing active research as a postdoctoral associate in the same university on low speed flow control using different actuation mechanisms. During his Ph.D. and postdoc studies, several projects on high/low speed wind tunnel testing were completed involving partners such as ESA, DSTL and EU FR7. Upon finishing the studies, Dr. Erdem started working for GE Aviation in Turkey in 2013 as thermal systems design lead engineer specializing on engine bay cooling and rotor-stator cooling in gas turbine engines. As of 2015, he is working for TUSAS Engine Industries (TEI) Inc., responsible for mainly thermal systems design comprised of secondary air systems, thermal analysis and component cooling.

In addition, he works on compression systems aerodynamics and extensive rig testing. Dr. Erdem’s role in Chief Engineers Office as a principal engineer involves overseeing/reviewing technical activities for the indigenous Turboshaft and Turbofan Engine Development programs related to his expertise.

Dr. Erdem acted as a reviewer of several international journals such as, Journal of Aerospace Engineering, Aerospace Journal, Journal of Aerospace Science and Technology, The Aeronautical Journal. Dr. Erdem is currently serving as an editor in Aerospace Journal and author/co-author of 12 journal and 36 conference articles and a book chapter with a citation count of 797 and H factor of 16.

Keynote: Key Technologies for Gas Turbine Engines for Aviation and Engine Development Programs at TUSAS ENGINE INDUSTRIES (TEI), TURKIYE

Abstract:

Modern commercial gas turbine engines for aviation are pushed to the limits of thermal efficiency in terms of pressure ratio and turbine inlet temperatures, only better materials such as CMCs coupled with sophisticated cooling technologies can further increase turbine inlet temperatures by 400K or more, resulting in increased cycle efficiencies.

On the other hand, improvement of propulsive efficiency can be accomplished with increasing by-pass ratio, which implies bigger fan diameters and/or smaller core sections. There is certainly room up to bypass ratio of 15, beyond that the use of nacelle is detrimental in terms aircraft drag, hence unducted configurations are favoured. On the military side, higher turbine inlet and afterburner temperatures help to reduce the engine size significantly, which shall be embedded inside an airframe. The gain in thermal efficiency with increased firing temperatures is non-negligible, moreover by-pass ratio improvement (inversely proportional to fan pressure ratio) and/or overall pressure ratio improvement can help to improve specific fuel consumption at various phases of the flight mission at the expense of specific thrust. TEI has been active in R&D for last 25 years with an increased impetus in last 10 years involving indigenous turbojet, turboshaft and turbofan engine development programs. The progress is on-going and multiple engines have been tested with success.