Crater Wall Flow-Like Features (Moon, Asteroids)

Author(s):  
Tamás Börzsönyi ◽  
Henrik Hargitai
Keyword(s):  
Author(s):  
Tamás Börzsönyi ◽  
Henrik Hargitai
Keyword(s):  

1975 ◽  
Vol 40 (10) ◽  
pp. 3145-3152 ◽  
Author(s):  
J. Prchlík ◽  
J. Soukup ◽  
V. Zapletal ◽  
V. Růžička ◽  
P. Kovařík

2013 ◽  
Vol 773 ◽  
pp. 749-754
Author(s):  
Zhen Ya Duan ◽  
Fu Lin Zheng ◽  
Hui Ling Shi ◽  
Jun Mei Zhang

In this paper, the numerical model of multi-stage liquid column scrubber was established. The flow field of liquid column scrubber with different inlet structure was respectively simulated by a commercial CFD code, Fluent. Considering the distribution characteristics of static pressure and velocity in the scrubber, this inlet type, single horizontal gas inlet with a notch at the bottom, is regarded as the most reasonable structure. On one hand, that structure has uniform distribution of static pressure. On the other hand, the velocity profile of its field presents saddle shape, i.e. the low central velocity exists between two peaks, which could contribute to weakening wall-flow phenomenon and obtaining uniform gas-liquid distribution.


2005 ◽  
Vol 81 (2) ◽  
pp. 146-178 ◽  
Author(s):  
Vicki Moon ◽  
Jennifer Bradshaw ◽  
Richard Smith ◽  
Willem de Lange
Keyword(s):  

2006 ◽  
Vol 45 (10) ◽  
pp. 3520-3530 ◽  
Author(s):  
Christos K. Dardiotis ◽  
Onoufrios A. Haralampous ◽  
Grigorios C. Koltsakis

Author(s):  
Thomas E. Dyson ◽  
David B. Helmer ◽  
James A. Tallman

This paper presents sliding-mesh unsteady CFD simulations of high-pressure turbine sections of a modern aviation engine in an extension of previously presented work [1]. The simulation included both the first and second stages of a two-stage high-pressure turbine. Half-wheel domains were used, with source terms representing purge and film flows. The end-wall flow-path cavities were incorporated in the domain to a limited extent. The passage-to-passage variation in thermal predictions was compared for a 1D and 2D turbine inlet boundary condition. Substantial impact was observed on both first and second stage vanes despite the mixing from the first stage blade. Qualitative and quantitative differences in surface temperature distributions were observed due to different ratios between airfoil counts in the two domains.


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