Development of a high-fideliity transient aerothermal model for a helicopter turboshaft engine for inlet distortion and engine deterioration simulations

Novikov, Yaroslav
Presented in this thesis is the development of a high-fidelity aerothermal model for GE T700 turboshaft engine. The model was constructed using thermodynamic relations governing change of flow properties across engine components, and by applying real component maps for the compressor and turbines as well as empirical relations for specific heats. Included in the model were bleed flows, turbine cooling and heat sink effects. Transient dynamics were modeled using inter-component volumes method in which mass imbalance between two engine components was used to calculate the inter-component pressure. This method allowed fast, high-accuracy and iteration-free calculation of engine states. Developed simulation model was successfully validated against previously published simulation results, and was applied in the simulation of inlet distortion and engine deterioration. Former included simulation of steady state and transient hot gas ingestion as well as transient decrease in the inlet total pressure. Engine deterioration simulations were performed for four different cases of component deterioration with parameters defining engine degradation taken from the literature. Real time capability of the model was achieved by applying time scaling of plenum volumes which allowed for larger simulation time steps at very little cost of numerical accuracy. Finally, T700 model was used to develop a generic model by replacing empirical relations for specific heats with temperature and FAR dependent curve fits, and scaling T700 turbine maps. Developed generic aerothermal model was applied to simulate steady state performance of the Lycoming T53 turboshaft engine.


Development of a cycle design software for turboshaft engines
Erk, Mert; Aksel, Mehmet Haluk; Department of Mechanical Engineering (2015)
In this thesis, a computer software for the cycle design of a turboshaft engine is developed. Firstly, a numerical air model was implemented and the model of the turboshaft to be used in the simulation was selected. The first requirement for the software is the capability of performing design point calculations and parametric studies. This feature, which is the initial part of an aircraft engine design, was integrated into the software. At this point, to have a better estimation of the component performance...
Numerical simulation of turbine internal cooling and conjugate heat transfer problems with Rans based turbulance models
Görgülü, İlhan; Akmandor, İbrahim Sinan; Department of Aerospace Engineering (2012)
The present study considers the numerical simulation of the different flow characteristics involved in the conjugate heat transfer analysis of an internally cooled gas turbine blade. Conjugate simulations require full coupling of convective heat transfer in fluid regions to the heat diffusion in solid regions. Therefore, accurate prediction of heat transfer quantities on both external and internal surfaces has the uppermost importance and highly connected with the performance of the employed turbulence mode...
Elfarra, Monier A.; Akmandor, I. Sinan; Sezer Uzol, Nilay (2011-03-25)
The main purpose of this paper is to optimize winglet geometry by using CFD with Genetic Algorithm and study its effects on power production. For validation and as a baseline rotor, the NREL Phase VI wind turbine rotor blade is used. The Reynolds-Averaged Navier-Stokes equations are solved and different turbulence models including the Spalart-Allmaras, k-epsilon Launder-Sharma, k-epsilon Yang-Shih and SST k-omega models are used and tested. The results of the power curve and the pressure distribution at dif...
Development of aero-thermodynamic cycle design code for turboshaft engines and investigation of fouling effects on performance
Sadıkoğlu, Umut; Baran, Özgür Uğraş; Baş, Onur; Department of Mechanical Engineering (2022-8-04)
In this thesis, a turboshaft engine performance analysis code is developed on MATLAB. Furthermore, compressor map generation from limited data and deterioration effects on the engine performance are investigated. It is considered that the first step of designing a gas turbine is the selection of the aero-thermodynamic cycle. For this purpose, design point analysis with the parametric design capability is conducted and engine limits are determined. Subsequently, off-design analyses are initiated. During the ...
Development of a high fidelity finite element model of a wind turbine blade via modal testing
Amer, Chadi; Şahin, Melin; Department of Aerospace Engineering (2015)
The design of an optimised horizontal axis 5-meter-long wind turbine rotor blade, is a research and development project, in order to fulfil the requirements of high efficiency torque-from-wind production. For this purpose, a research study is presented here, by investigating the structural characteristics of a composite wind turbine blade via finite element modelling and experimental modal analysis. At first, modal tests are performed by using various sensor-actuator pair combinations. After that the geomet...
Citation Formats
Y. Novikov, “Development of a high-fideliity transient aerothermal model for a helicopter turboshaft engine for inlet distortion and engine deterioration simulations,” M.S. - Master of Science, Middle East Technical University, 2012.