Preliminary Simulation of a 3D Turbine Stage with In Situ Combustion Sterian DANAILA 1,a * , Dragos ISVORANU 1,b and Constatin LEVENTIU 1,c 1 Elie Carafoli Dept. of Aerospace Sciences, University Politehnica of Bucharest, 1, Gheorghe Polizu Street, 011061-Bucharest, ROMANIA a sterian.danaila@upb.ro, b dragos.isvoranu@upb.ro, c cleventiu@yahoo.com Keywords: turbine in situ combustion, rotor-stator interaction. Abstract. This paper presents the preliminary results of the numerical simulation of flow and combustion in a one stage turbine combustor (turbine stage in situ combustion). The main purpose of the simulation is to assess the stability of the in situ combustion with respect to the unsteadiness induced by the rotor-stator interaction. Apart from previous attempts, the salient feature of this CFD approach is the new fuel injection concept that consisting of a perforated pipe placed at mid-pitch in the stator row passage. The flow and combustion are modelled by the Reynolds-averaged Navier- Stokes equations coupled with the species transport equations. The chemistry model used herein is a two-step, global, finite rate combustion model while the turbulence model is the shear stress transport model. The chemistry turbulence interaction is described in terms of eddy dissipation concept. Introduction Currently, research in fossil fuels energy production is confronted with the issue of large levels of pollutants emissions and green house effects. National and worldwide energy consumption shows an increasing trend which, in order to satisfy this demand in corroboration with maintaining or reduction the levels of pollutants emissions, leads to a growing awareness to increase the efficiency of power production systems and/or reconsideration of several aspects of fossil fuels combustion. The present technology in turbo engines is to burn fuel in the combustion chamber and occasionally in the aft-turbine post-combustion chamber. Current conventional developments of gas turbine aero- thermodynamics provide small efficiency and power increase, because with the present technology one reached an asymptotical convergence to the upper limit of the gas turbine performance. This asymptotical convergence implies that large efforts to ameliorate the aerothermodynamics result in rather small improvements. Turbine combustion provides a paradigm shift and a step change in gas turbine aerothermodynamics. A turbine-combustor is defined as a turbine in which fuel is injected and burned (Fig.1). The process of combustion in the turbine is called in situ reheat. Thermodynamic cycle, (a hybrid between the Ericsson and Brayton cycles) analyses have demonstrated the benefits of using reheat in the turbine in order to increase specific power and thermal efficiency. In fact, the leading study of Sirignano and Liu [1] compares the performance of a jet engine using traditional compression together with isothermal expansion. Their analysis included the Specific Thrust (ST) and Thrust Specific Fuel Consumption (TSFC) for several layouts including a traditional jet engine (no afterburner, no turbine burner), a jet engine supplemented with an afterburner and a jet engine with turbine burner. Usually, ST is inverse proportional to the size/weight of the jet engine while TSFC scales with the fuel consumption per unit thrust. For low speed transport, the TSFC shows that the turbine burner uses less fuel than an afterburner supplemented engine but more than a traditional jet Applied Mechanics and Materials Vol 772 (2015) pp 103-107 Submitted: 2015-02-09 © (2015) Trans Tech Publications, Switzerland Revised: 2015-02-12 doi:10.4028/www.scientific.net/AMM.772.103 Accepted: 2015-02-26 All rights reserved. No part of contents of this paper may be reproduced or transmitted in any form or by any means without the written permission of Trans Tech Publications, www.ttp.net. (ID: 109.99.107.193-21/04/15,17:28:00)