Development of aero-thermodynamic cycle design code for turboshaft engines and investigation of fouling effects on performance

Download

Umut Sadikoglu Thesis.pdf

Date

2022-8-04

Author

Sadıkoğlu, Umut

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

993
views

594
downloads

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 off-design analyses, component performance maps are scaled according to the design point analysis results. Construction of the performance maps is followed by determining the matching points of the components with varying operating conditions. Then, the engine performance during transitions is examined using the polar moments of inertia of the components and fuel flow outputs of the off-design analyses. Steady-state and transient performance analyses mentioned up to this point is verified by GasTurb 14. For the validation of the code, the General Electric T700 engine is chosen. The developed code is then combined with the compressor performance map generation method called stage-stacking. The General Electric LM2500-30 engine is used for the stage stacking algorithm due to access to its running line and flow field geometry data. Lastly, stage fouling effects on the performance parameters are evaluated for the compressor section. For this purpose, a modified version of the method suggested by MacIsaac is used. Once the clean and fouled maps of the compressor are obtained, steady-state and transient performance analyses are performed to assess the effect of compressor fouling on overall engine performance.

Subject Keywords

Helicopter turboshaft engine, Gas turbine performance modeling, Thermodynamic matching model, Gas turbine performance deterioration, Stage-stacking technique

URI

https://hdl.handle.net/11511/98704

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

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...
INVESTIGATION AND OPTIMIZATION OF WINGLETS FOR HAWT ROTOR BLADES 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...
Design and performance analysis of a pump-turbine system using computational fluid dynamics Yıldız, Mehmet; Albayrak, Kahraman; Çelebioğlu, Kutay; Department of Mechanical Engineering (2011) In this thesis, a parametric methodology is investigated to design a Pump-Turbine system using Computational Fluid Dynamics ( CFD ). The parts of Pump-Turbine are created parametrically according to the experience curves and theoretical design methods. Then, these parts are modified to obtain 500 kW turbine working as a pump with 28.15 meters head. The final design of Pump-Turbine parts are obtained by adjusting parameters according to the results of the CFD simulations. The designed parts of the Pump-Turbi...
Development of a high-fideliity transient aerothermal model for a helicopter turboshaft engine for inlet distortion and engine deterioration simulations Novikov, Yaroslav; Uzol, Oğuz; Kutay, Ali Türker; Department of Aerospace Engineering (2012) 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 i...
Developing an HLA-based naval maneuvering simulation Topcu, O; Oğuztüzün, Mehmet Halit S. (Wiley, 2005-12-01) This paper discusses the main issues involved in developing a high level architecture (HLA)-based distributed simulation while presenting an application called Naval Surface Tactical Maneuvering Simulation System (NSTMSS), which is intended to serve as a testbed for HLA and distributed interactive simulation (DIS) research. NSTMSS provides a networked virtual environment (NVE) for naval surface actions in which new formations can be evaluated and tested and present ones can be practiced and analyzed. This p...

Citation Formats

U. Sadıkoğlu, “Development of aero-thermodynamic cycle design code for turboshaft engines and investigation of fouling effects on performance,” M.S. - Master of Science, Middle East Technical University, 2022.