Design and analysis of annular combustion chamber of a low bypass turbofan engine in a jet trainer aircraft  

作　　者：C.Priyant Mark A.Selwyn 

机构地区：[1]Department of Aerospace Engineering,Karunya University,Coimbatore,T.N.,India [2]A.E.R.D.C.,Hindustan Aeronautics Ltd.,Bangalore,KA,India

出　　处：《Propulsion and Power Research》2016年第2期97-107,共11页推进与动力（英文）

摘　　要：The design of an annular combustion chamber in a gas turbine engine is thebackbone of this paper.It is specifically designed for a low bypass turbofan engine in a jettrainer aircraft.The combustion chamber is positioned in between the compressor and turbine.lt has to be designed based on the constant pressure,enthalpy addition process.The presentmethodology deals with the computation of the initial design parameters from benchmarking ofreal-time industry standards and arriving at optimized values.It is then studied for feasibilityand finalized.Then the various dimensions of the combustor are calculated based on differentempirical formulas.The air mass flow is then distributed across the zones of the combustor.The cooling requirement is met using the cooling holes.Finally the variations of parameters atdifferent points are calculated.The whole combustion chamber is modeled using Siemens NX8.0,a modeling software and presented.The model is then analyzed using various parametersat various stages and levels to determine the optimized design.The aerodynamic flowcharacteristics is simulated numerically by means of ANSYS 14.5 software suite.The air-fuelmixture,combustion-turbulence,thermal and cooling analysis is carried out.The analysis isperformed at various scenarios and compared.The results are then presented in image outputsand graphs.

关 键 词：Aerodynamic design Annular combustion chamber CFD(computational fluid dynamics)analysis Gas tur bine engine Optimization Real-time model 

分 类 号：TP3[自动化与计算机技术—计算机科学与技术]