This paper presents the preliminary design of a three stage fan for a twin-spool low bypass ratio... more This paper presents the preliminary design of a three stage fan for a twin-spool low bypass ratio turbofan aeroengine. Design produre has been initialized with the specification of technical requirements obtained from the parametric cycle analysis. With this information, a suitable baseline engine is selected that has the closest technical specifications. The design process continues with the determination of the number of fan stages and other stage parameters. The next step is the designation of the blade airfoil profiles such that they have adequate stall margin in subsonic conditions. Airfoils are designed to avoid both positive and negative stall situations. Hub profiles have noticeably larger cambers due to lower linear speeds in comparison to tip profiles. By stacking up airfoil profiles in the radial direction form hub to tip a quasi three dimensional design is reached. Finally, solid models of the rotor and the stator parts were produced.
... showed the possibility of stabilizing the oscillations of acoustic mode in natural gas turbin... more ... showed the possibility of stabilizing the oscillations of acoustic mode in natural gas turbine combustor by ... is a conical section, which contracts the exhaust flow down to an exit diameter of ... high and low values, and the residence time associated with the high temperature region is ...
In order to initiate the design process for a new aeroengine, it would be necessary that a matchi... more In order to initiate the design process for a new aeroengine, it would be necessary that a matching study be performed between the aircraft under design and its prospective power plant. In this work wing loading and engine thrust reqiurements are determined. Within this context thrust level is determined for a fighter jet whose mission profile is pre-determined. While the mission profile is being decided upon a typical first-day-of-the-war mission scenario for a new generation fighter aircraft is considered. Mission legs were handled individually and the solution space is restricted by drawing the corresponding constraint curve for each one. A point within the feasible solutions region is selected regarding the state-of-the-art. For the determined mission profile the appropriate sea level thrust to take-off weight ratio .... happens to be around 1.2. At the design point the selected thrust loading .... is 7.0 kPa. As a result of mission analysis it has been observed that the aircaft...
Bir yakitin havayi en az kirletecek sekilde yanmasi oldukca onemlidir. Her gun bu konu ile ilgili... more Bir yakitin havayi en az kirletecek sekilde yanmasi oldukca onemlidir. Her gun bu konu ile ilgili kirletici gaz salimlarini kisitlayan yeni yasal duzenlemeler yururluge girmektedir. Ikinci bir onemli konu da yuksek yogunlukta hacimsel isi aciga cikisini elde etmektir. Gozenekli ortamda yanma bu iki onemli konuda cozum uretebilmektedir. Bu calismada, cesitli sayisal analizler yapilarak isil verimlilik ve yanma, 5kW’lik gozenekli ortamda simetrik ve iki boyutlu bir problem seklinde incelenmistir. Cozum alani dort adet alt-alandan olusmaktadir; iki art arda gozenekli ortam (ilki dusuk poroziteli, ikincisi yuksek poroziteli), sabit akis hizina sahip bir su tanki ve kati duvar. Yanmada tepkimeye girenler olarak metan-hava karisimi degisik fazla hava katsayilarinda kullanilmistir ve yakici tasariminin en iyilenmesi amaciyla cesitli su akis debileri her bir esdegerlik orani icin test edilmistir. Navier-Stokes, enerji (isil denge modeli) ve tur denklemleri iki boyutlu simetrik modelimiz ici...
Turbulent swirl stabilized methane/air flames were studied to investigate the flame front charact... more Turbulent swirl stabilized methane/air flames were studied to investigate the flame front characteristics. Swirl number and equivalence number were selected as 0.74 and 0.7 respectively. This study is mainly based on image processing algorithms. Therefore flame front information is recovered from Mie scattering images. Flame edges were detected by Canny edge detection algorithm. Statistical analysis was applied to instantaneous flame front areas and velocity vectors which were provided from Mie scattering images. In addition, fractal approach was employed to the flame front areas to predict the wrinkling factor thus the turbulent flame speed. As a consequence flame front was stabilized both on the edge of the inner and outer shear layer. Turbulent burning velocity was provided on the flame front by superposition of flame front found from Mie images and velocity data analyzed from Particle Image Velocimetry (PIV). Furthermore, flame area ratios were procured to reason the flame front...
This paper presents the preliminary design of a three stage fan for a twin-spool low bypass ratio... more This paper presents the preliminary design of a three stage fan for a twin-spool low bypass ratio turbofan aeroengine. Design produre has been initialized with the specification of technical requirements obtained from the parametric cycle analysis. With this information, a suitable baseline engine is selected that has the closest technical specifications. The design process continues with the determination of the number of fan stages and other stage parameters. The next step is the designation of the blade airfoil profiles such that they have adequate stall margin in subsonic conditions. Airfoils are designed to avoid both positive and negative stall situations. Hub profiles have noticeably larger cambers due to lower linear speeds in comparison to tip profiles. By stacking up airfoil profiles in the radial direction form hub to tip a quasi three dimensional design is reached. Finally, solid models of the rotor and the stator parts were produced.
... showed the possibility of stabilizing the oscillations of acoustic mode in natural gas turbin... more ... showed the possibility of stabilizing the oscillations of acoustic mode in natural gas turbine combustor by ... is a conical section, which contracts the exhaust flow down to an exit diameter of ... high and low values, and the residence time associated with the high temperature region is ...
In order to initiate the design process for a new aeroengine, it would be necessary that a matchi... more In order to initiate the design process for a new aeroengine, it would be necessary that a matching study be performed between the aircraft under design and its prospective power plant. In this work wing loading and engine thrust reqiurements are determined. Within this context thrust level is determined for a fighter jet whose mission profile is pre-determined. While the mission profile is being decided upon a typical first-day-of-the-war mission scenario for a new generation fighter aircraft is considered. Mission legs were handled individually and the solution space is restricted by drawing the corresponding constraint curve for each one. A point within the feasible solutions region is selected regarding the state-of-the-art. For the determined mission profile the appropriate sea level thrust to take-off weight ratio .... happens to be around 1.2. At the design point the selected thrust loading .... is 7.0 kPa. As a result of mission analysis it has been observed that the aircaft...
Bir yakitin havayi en az kirletecek sekilde yanmasi oldukca onemlidir. Her gun bu konu ile ilgili... more Bir yakitin havayi en az kirletecek sekilde yanmasi oldukca onemlidir. Her gun bu konu ile ilgili kirletici gaz salimlarini kisitlayan yeni yasal duzenlemeler yururluge girmektedir. Ikinci bir onemli konu da yuksek yogunlukta hacimsel isi aciga cikisini elde etmektir. Gozenekli ortamda yanma bu iki onemli konuda cozum uretebilmektedir. Bu calismada, cesitli sayisal analizler yapilarak isil verimlilik ve yanma, 5kW’lik gozenekli ortamda simetrik ve iki boyutlu bir problem seklinde incelenmistir. Cozum alani dort adet alt-alandan olusmaktadir; iki art arda gozenekli ortam (ilki dusuk poroziteli, ikincisi yuksek poroziteli), sabit akis hizina sahip bir su tanki ve kati duvar. Yanmada tepkimeye girenler olarak metan-hava karisimi degisik fazla hava katsayilarinda kullanilmistir ve yakici tasariminin en iyilenmesi amaciyla cesitli su akis debileri her bir esdegerlik orani icin test edilmistir. Navier-Stokes, enerji (isil denge modeli) ve tur denklemleri iki boyutlu simetrik modelimiz ici...
Turbulent swirl stabilized methane/air flames were studied to investigate the flame front charact... more Turbulent swirl stabilized methane/air flames were studied to investigate the flame front characteristics. Swirl number and equivalence number were selected as 0.74 and 0.7 respectively. This study is mainly based on image processing algorithms. Therefore flame front information is recovered from Mie scattering images. Flame edges were detected by Canny edge detection algorithm. Statistical analysis was applied to instantaneous flame front areas and velocity vectors which were provided from Mie scattering images. In addition, fractal approach was employed to the flame front areas to predict the wrinkling factor thus the turbulent flame speed. As a consequence flame front was stabilized both on the edge of the inner and outer shear layer. Turbulent burning velocity was provided on the flame front by superposition of flame front found from Mie images and velocity data analyzed from Particle Image Velocimetry (PIV). Furthermore, flame area ratios were procured to reason the flame front...
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Papers by Onur Tuncer