Abstract
This paper presents a numerical investigation of the unsteady transport phenomena in a turbine-combustor. The flow and combustion are modeled by the Reynolds-averaged Navier-Stokes equations coupled with the species conservation equations. The chemistry model used herein is a two-step, global, finite rate combustion model for methane and combustion gases. The governing equations are written in the strong conservation form and solved using a fully implicit, finite difference approximation. This numerical algorithm has been used to investigate the airfoil temperature variation and the unsteady blade loading in a four-stage turbine-combustor. The numerical simulations indicated that in situ reheat increased the turbine power by up to 5.1%. The turbine combustion also increased blade temperature and unsteady blade loading. Neither the temperature increase nor the blade loading increase exceeded acceptable values for the turbine investigated.
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Flitan, H.C., Cizmas, P.G., Lippert, T., Bachovchin, D., Little, D. (2006). ANALYSIS OF UNSTEADY AEROTHERMODYNAMIC EFFECTS IN A TURBINE-COMBUSTOR. In: Hall, K.C., Kielb, R.E., Thomas, J.P. (eds) UNSTEADY AERODYNAMICS, AEROACOUSTICS AND AEROELASTICITY OF TURBOMACHINES. Springer, Dordrecht. https://doi.org/10.1007/1-4020-4605-7_40
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DOI: https://doi.org/10.1007/1-4020-4605-7_40
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