Pürmüz tipi bir sıvı yakıtlı roket motoru ateşleyicisinin deneysel ve sayısal yöntemlerle incelenmesi ile bir performans parametresi olarak etkin alev boyunun elde edilmesi.

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Tezin Türü: Yüksek Lisans

Tezin Yürütüldüğü Kurum: Orta Doğu Teknik Üniversitesi, Mühendislik Fakültesi, Makina Mühendisliği Bölümü, Türkiye

Tezin Onay Tarihi: 2019

Öğrenci: Levent Çağatay Öz

Danışman: ABDULLAH ULAŞ

Özet:

In the scope of this thesis, the impact of operating conditions on the performance of an augmented spark igniter in means of effective length of the flame developed by the igniter and thermal energy output of it, by using numerical and experimental techniques, is examined. The igniter uses gaseous oxygen as oxidizer and gaseous hydrogen as fuel. Tests were carried out for 3 different oxygen mass flow rate to fuel mass flow rate ratios, and at each ratio with four different total mass flow rates. Experimental data were collected by schlieren imaging of the plume, thermocouples at different points in the plume and pressure transducer that is connected to the combustion chamber of the igniter. A numerical model was constructed and three dimensional numerical analyses for flow and combustion with detailed reaction mechanism were conducted for all test points. Later, the numerical model is validated using experimental data. Lastly, the performance parameters were defined and evaluated by the numerical model.