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دسته بندی:
مهندسی مکانیک - mechanical engineering
سال انتشار:
2016
عنوان انگلیسی مقاله:
Experimental Investigation on ignition schemes of a supersonic combustor with the rearwall-expansion cavity
ترجمه فارسی عنوان مقاله:
آزمایش تجربی بر روی طرح های احتراق یک آتش سوزی فوق العاده با حفره rearwall-expansion
منبع:
Sciencedirect - Elsevier - Acta Astronautica,Accepted manuscript,doi:10:1016/j:actaastro:2016:03:008
نویسنده:
Zun Cai, Yixin Yang, Mingbo Sun, Zhenguo Wang*
چکیده انگلیسی:
In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under
inflow conditions of Ma=2.52 with stagnation pressure P0=1.6Mpa and stagnation temperature T0=1486K. It is concluded
that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful
ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise
injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is
more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the
combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct
spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes.
Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be
affected substantially by the heat release in the combustor during a robust combustion process, which is important for the
prevention of thermal choking and the unstart of scramjet inlet.
Keywords:Rearwall-expansion cavity| ignition scheme| cavity direct spanwise injection| cavity upstream transverse injection
قیمت: رایگان
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