1.1 Computational Fluid Dynamics (CFD) Analyzer Development (Compressor & Turbine)
Engine manufacturers all over the world, especially in Turbomachinery design, use their own original CFD analyzer
and develop these analyzers to design competitive engines.
In the rig testing centers which will be installed prior to turboshaft engine program, all the necessary test data will be gathered to improve the analyzer. Accordingly, CFD analyzer will be developed and will be improved by the incoming data from the rig tests. Goal of this CFD analyzer is to create an analyzer which will be an alternative to the commercial code that will be used in the first stage of the turboshaft engine program. Then the use of these codes will directly take place in the future engine design activities.
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. 2D RANS analyzer development: 2D RANS analyzer development (by using a commercial mesh generator )and , making a comparison of the blade profiles which will be tested for the turboshaft project.
ii. Mesh generator development
iii. 3D RANS analyzer development: 3D RANS analyzer development (by using a commercial mesh generator )and , making a comparison of the blade profiles which will be tested for the turboshaft project.
iv. Validation: Validation of the original code with data obtained from rig testing and the necessary improvements will be done.
1.2 Blade Geometry Optimization (Compressor & Turbine)
To achieve a turbomachinery design with a high performance, design parameters which will impact the overall design must be known very well. This project will help the designer to investigate the effects of these parameters. The design optimization software will be developed to enable improvement.
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. 2D Blade Optimization: To reduce the aerodynamic losses of two-dimensional blade model, an optimization software will be developed. From the literature,a blade profile with the known details (eg VKI-LS89 blade profile for Turbine) will be selected for the model. The aerodynamic performance of the model will be determined by using CFD software and results will be compared with literature data. Developed software will be used to improve the performance of the selected model
ii. 3D Blade Optimization: Aim is to develop the necessary tools to optimize the performance of 3d model of the blade.
Three-dimensional geometry of a fin will be created by using the model selected as a two-dimensional optimization
The performance of this geometry will be determined by CFD software and it's aerodynamic performance aimed to improved by to be developed software.
1.3 CFD Analysis Applications (Combustion Chamber - RANS, LES, Ignition, conjugate heat transfer, Flame Stability)
In combustion modeling and numerical analysis, realistic analysis of the turbulence-combustion interaction and in terms of detailed studying of time-dependent effects, LES (Large Eddy Simulation) approach has become a powerful tool in both academic and industrial fields.LES method has a critical importance in the simulations of the events like Ignition, flame stability. As a result of this R&D work, It being expected to develop the methods and applications following below. The methods to be developed are expected to be oriented in to the actual application.
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. Determination of reactive LES methodology: To determine the reactive flow which occurs in the combustion chamber by using LES modeling methods with applying appropriate fuel type and chemistry. Applying the developed methodology on a actual operating conditions of a combustion chamber model .
ii. Modeling of Transient Combustion Event: Modeling of ignition, flame stability and combustion/deflation events which occurs instantaneously in the combustion chamber by LES methods.
iii. Conjugate Heat Transfer Solutions: To Identify the combustion-induced heating that occurs in the combustion chamber walls by conjugate heat transfer solutions . Determining the impact of the reactive flow solution to the wall temperature.
1.4 Fuel Injector Development (Combustion Chamber - Design, Analysis, Production, Testing)
One of the most important factor that is affecting the actual combustion and flow characteristics in the gas turbine combustion chamber is the fuel injector. Because of their special design fuel injectors provide at a desired diameter of fuel droplets, flow rate ,cone angle, speed, fuel outlet. Within the scope of the project, a suitable liquid fuel injector is required to be designed
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. Design: Analytical methods that has been used in the design process, developed codes , implemented CFD analysis to be presented in detail and to transform the design methodology into a repeatable process.
ii. Production: The production of the designed nozzle. Submission of the production drawings and manufacturing of details of the injectors. Determining different production methods can be used.
iii. Test: produced by the injector give the desired flow rate and the target pressure range shown with a uniform atomisation test was carried out. The realization of the characterization tests carried out without burning hot and the investigation of the performance in a test environment where the injector is burning.
1.5 Impeller-Diffuser Interaction (radial compressor)
To achieve low fuel consumption in 1000-1500hp class turbo shaft engines,compressors that have high compression ratio and a high efficiency are needed. However, compressors that are simple, with less parts and easy to manufacture are being preferred in engines of this class. In helicopter applications due to the exposure of high inlet distortion, designs with high stall margin and long-lasting designs are important. In these engines, radial compressors are being preferred as they can more easily meet these demands.
In this project impeller-diffuser interaction which is one of the most important issues for the radial compressors will be investigated experimentally and numerically.
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. Numeric: In This study, development of the CFD analysis model, doing three-dimensional CFD analysis of the model, and comparing the CDF analysis with test results are being planned
ii. Experimental: Experimental studies will be performed in the test rig "TJ-90 turbojet engine Centrifugal Compressor Design Optimization" which will be set up within the scope of SanTez (
industrial theses support program which is being supported by government). The data obtained from the experiments will be used to compare with the numerical analysis.
1.6 High Performance Blade Tip Zone Design (Turbine)
The project aims primarily to understand the physics of the flow in the turbine rotor tip. Work will begin as experimental and in line with the conclusions made, the necessary methodology will be established for the modelling of this critical region by CFD. In the later stages of the study, analysis of the geometry to reduce the aerodynamic performance losses will be done by numeric methods.
Performance results of the best model will be shown with experimental activities. Experimental work to be done under the project will be carried out using turboshaft engine program to be established within the HPT cascade test rig.
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. Experimental investigation of the flow in the blade tip region for different clearances: different types of geometry found in the literature will be examined and detailed flow characteristics of the selected model's tip region will be determined. Works will be performed experimentally in the HPT cascade test rig. In this way, the physics of the flow from the high-pressure region to the low pressure region is aimed to be understood.
ii. Developing methods for the tip region CFD analysis: Best methodology to reflect the loss mechanisms in tip region will be established. The CFD analysis method which will solve the experimental tests correctly, is going be studied
iii. Determination of the high-performance tip model: Alternative tip geometry will be studied by using the CFD methodology that has been developed . The model that provides the best performance increase will be determined.
iv. Experimental characterization of the new design: Performance of selected new tip region will be experimentally determined. Experimental work will be carried in the HPT cascade testing rig. The performance increase will be experimentally determined by pressure measurement at the outlet and flow visualization techniques which will be applied on the tip region.
1.7 Effective cooling of the blade tip region (Turbine)
At high temperatures, turbine end regions is one of the fastest regions get damaged . This project aims to reduce the temperature of this region and developing a cooling design which is expected to make cooling more effective by using less cooling air. Experimental work to be done will be carried out by the HPT cascade test rig which will be established within the scope of the project.
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. Tip cooling concept design: The cooling configurations and the cooling methods which will be applied on to the tip geometry will be determined. Effective mechanisms in these methods will be understood and the configuration to increase the cooling efficiency will be established.
ii. Aerodynamic analysis: Alternative cooling configurations can be applied to the tip region shall be determined. These configurations will be determined by the flow properties analysis method. The model of the best alternative, will be tested in the HPT cascade testing rig and analysis results will be verified.
iii. Cooling Efficiency: The analysis methodology for determining the cooling efficiency will be improved by literature information. The cooling efficiency of the specified configurations will be determined by the analysis method. The model of the best alternative, will be tested in the HPT cascade testing rig and analysis results will be verified.
1.8 Cooling Performance Prediction (Turbine)
Determining the metal temperature of turbine blades under combustion chamber conditions and developing the code used for the determination of metal temperatures is being aimed. Design methodology's reliability is being aimed to increased, before the test of the engine.
The inclusion of the work packages of the project is planned to be presented under the following main headings.
i. Metal temperature prediction for cooled blade model: Temperature distribution of the inner-cooled turbine blades will be experimentally measured under similar conditions to the combustor exit temperature. Temperature levels in different regions will be determined and compared with predicted temperatures in the design. The test shall be repeated for different gas temperatures.
ii. Development of the code that calculates metal temperatures: A software that calculates metal temperatures according to the temperature distribution obtained from the tests will be developed. This software will calculate the metal temperatures, independently from the prior CFD analysis.
