ISSN (e): 2250 – 3005 || Volume, 08 || Issue, 8|| August – 2018 || International Journal of Computational Engineering Research (IJCER) www.ijceronline.com Open Access Journal Page 13 No Reaction Flow Analysis of Aero-Derivative Annular Combustor of a Turbo Shaft Engine Raja Marudhappan 1 , Udayagiri Chandrasekhar 2 , K Hemachandra Reddy 3 1 Research Scholar, JNTUA, Ananthapuramu - 515 002, India 2 Vel Tech University, Chennai- 600 062, India 3 JNTUA, Ananthapuramu – 515002, India Corresponding Author: Raja Marudhappan --------------------------------------------------------------------------------------------------------------------------------------- Date of Submission: 20-07-2018 Date of acceptance: 04-08-2018 --------------------------------------------------------------------------------------------------------------------------------------- I. INTRODUCTION The overall performance of a combustion chamber depends on proper supply of combustion air at right place, direction and quantity. The combustion air needs to be apportioned effectively to primary zone combustion to stabilize the flame, in secondary zone to maximize the burning rate and in the dilution zone for proper temperature reduction. The stabilization of flame near the injector solely depends on the formation and sustaining of recirculation zone around the injector. The major objectives of a combustion system is to reduce the velocity of incoming air and distribute to different zones to maintain uniform flow without parasitic losses to obtain maximum burning rate and desired pattern factor at the exit. The design of aero derivative combustion chamber is a challenging task to the researchers since the space available for combustion is very small. The researchers need to carefully assess proper mixing of incoming air with the hot gas to ensure flame stability and to reduce the pollutant emission and within acceptable noise level. The provisioning of several features considering aerodynamic and combustion requirements makes the combustor geometry more complex. The successful design of a combustion chamber requires the knowledge of flow recirculation, jet penetration and mixing. A good mixing is required in the primary zone for achieving high combustion rates by maintaining the emission meeting the statutory requirements. The dilution zone must provide proper jet penetration in order to supply hot gas to the turbine inlet with acceptable pattern factor. The penetration of dilution jet is improved by providing dilution tubes. This study focusses on the flow analysis on two different combustor configurations, one without dilution tubes and another with dilution tubes. A generic annular combustion chamber of a 1100 kW class aero derivative gas turbine is considered for the flow analysis. One configuration has combustion liner with plain holes and the other configuration has liner with extended tubes only in the dilution zone. The objective of this research is to perform cold flow analysis in a realistic annular combustor using commercial CFD code to obtain aerodynamic aspects of the flow at the design inlet pressure. ABSTRACT Two different configurations of annular combustor of a generic 1100 kW class aero-derivative gas turbine are subjected to steady state incompressible cold flow analysis. One model has combustion liner with plain holes and the other with plain holes in recirculation and primary zones and dilution tubes in dilution zone alone. The simplified computational domain is discretized with Polyhedral cells. The two equation k-Ɛ model is applied for simulating the turbulence with standard wall function. The Reynolds Averaged Navier-Stokes (RANS) equations are solved over the discretized domain using pressure based Semi-Implicit Method for Pressure Linked Equations(SIMPLE) and finite volume method. The calculated velocity fields at combustor exit, pressure contour and Streamlines on Meridional plane are presented. The generation of turbulent kinetic energy and its dissipation are presented and discussed. Though the experimental data on similar combustor models are not available in literature, the overall aerodynamic performance of combustors resembles typical proven annular combustor aerodynamics. KEYWORDS: Annular combustor, CFD, Turbo-shaft, Flow analysis, Turbulence, Streamlines, RANS