By Herbert Staedtke
The following, the writer, a researcher of exceptional event during this box, summarizes and combines the new effects and findings on complex two-phase stream modeling and numerical equipment another way dispersed in a number of journals, whereas additionally delivering reasons for numerical and modeling suggestions formerly now not coated by means of different books. The ensuing systematic and accomplished monograph is unrivalled in its sort, serving as a reference for either researchers and engineers operating in engineering in addition to in environmental technology.
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Additional info for Gasdynamic Aspects of Two-Phase Flow-Hyperbolicity Wave Propagation Phenomena and Related N
D) With the further decrease of the exit pressure the position of the shock waves moves further downstream and for pexit = p3 , the shock has reached the exit plane. Any further decrease of the exit pressure then has no effect any longer on the nozzle flow. For the case of ideal state equations the critical conditions (M = 1) can be immediately given as a function of the upstream reservoir condition as 2 Tcr = T0 κ+1 κ/(κ−1) 2 . 5 Flow through convergent–divergent nozzles 23 Fig.
Nevertheless, homogeneous two-phase flow models can be seen as special limiting cases for more detailed approaches and, for this reason, they are very helpful for the understanding of more complex conditions. 1 Homogeneous equilibrium model The homogeneous equilibrium model for two-phase flow is based on the assumption of infinite transfer processes between the phases for mass, momentum, and energy, which results in equal local (average) flow velocities and equal local (average) temperatures for the two phases.
The transient is initiated by an instantaneous removal of the diaphragm. 106) and pR > pL . high pressure region: U = UL removable diafragm low pressure region: U = UR xdia x Fig. 13: Shock tube test problem If viscous effects are ignored a self-similar solution exists where all parameters are only functions of the ratio x/t as illustrated in Fig. 14. Three different wave phenomena can be distinguished which separate the uniform regions 1, 2, 3, and 4: (1) a shock wave propagating into the low pressure region, followed by (2) a contact discontinuity traveling with subsonic velocity into the right-hand side of the pipe, and (3) a centered rarefaction wave (expansion fan) propagating into the high pressure region.