Design of a high pressure turbine nozzle guide vane with effective film cooling system on leading edge

Abstract

The fast development in the field of aeronautics dictates development of more powerful aircraft engines. Constant increase in overall pressure ratios and operating temperatures are essential for the required higher power and thrust.. However, higher Turbine Entry Temperatures reduce the operation life of engine components. Cooling of engine components is one of the vital issues for development of efficient engines in terms of engine life and cost. Gas turbine cooling technologies have been investigated for more than 70 years and it has substantially changed in the course of new aircraft engine development. In this study, a nozzle guide vane (NGV) is designed and an efficient cooling system is investigated for a commercial aircraft engine NGV leading edge. The engine is developed for “AIAA Undergraduate Team Engine Design Competition” and it has extremely a high overall pressure ratio of 60. The cooling of NGV, Nozzle Guide Vane, is one of the most critical design issues in the whole engine design cycle. In the present study film cooling of an NGV is investigated using computational fluid dynamics (CFD). Parametric study of different cooling hole configurations with a study of different turbulence sub models are studied. The parametric study of film cooling includes the cooling hole types, hole numbers and positions. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All right reserved.