Research on the relative flow evacuation method of staircase based on massmotion

2021 ◽  
Author(s):  
Hu Zhou ◽  
Daoliang Zhao ◽  
Yun Lu
Keyword(s):  
Relative Flow

Relative Flow of Bacteria and Oil in Porous Media

2017 ◽  
Vol 3 (02) ◽  
pp. 98-106
Author(s):  
Abdulrazag Y Zekri ◽  
Mamdouh Gannam ◽  
Mohmed Nasr ◽  
Amer M Aborig
Keyword(s):  
Porous Media ◽  
Relative Flow

Stability of Interfaces with Self‐Gravity, Relative Flow, andBField

1998 ◽  
Vol 508 (2) ◽  
pp. 680-689 ◽  
Author(s):  
James H. Hunter, Jr. ◽  
Rodney W. Whitaker ◽  
Richard V. E. Lovelace
Keyword(s):  
Self Gravity ◽  
Relative Flow

Unsteady Flow Phenomena in Rotating Centrifugal Impeller Passages

1970 ◽  
Vol 92 (1) ◽  
pp. 65-71 ◽  
Author(s):  
E. Lennemann ◽  
J. H. G. Howard
Keyword(s):  
Unsteady Flow ◽  
Secondary Flow ◽  
Centrifugal Impeller ◽  
Bubble Flow ◽  
Hydrogen Bubble ◽  
Visualization Technique ◽  
Rotating Systems ◽  
Flow Phenomena ◽  
Relative Flow ◽  
Zero Flow

The phenomena of unsteady relative flow observed in a centrifugal impeller passage running at part capacity and zero flow are discussed. The mechanisms of passage stall for a shrouded and unshrouded impeller are investigated and a qualitative correlation is developed for the influence of secondary flow and inducer flow on the passage stall. The hydrogen bubble flow visualization technique is extended to higher velocities and rotating systems and provides the method for obtaining the experimental results.

Interaction Between Impeller and Volute of Pumps at Off-Design Conditions

1986 ◽  
Vol 108 (1) ◽  
pp. 12-18 ◽  
Author(s):  
J. A. Lorett ◽  
S. Gopalakrishnan
Keyword(s):  
Analytical Solution ◽  
Flow Behavior ◽  
Cyclic Variation ◽  
Test Results ◽  
Flow Parameters ◽  
Pump Output ◽  
Simplifying Assumptions ◽  
Radial Thrust ◽  
Relative Flow ◽  
Good Agreement

In a centrifugal pump of volute type, the respective characteristics of the impeller and the volute are such that at only one operating point can the flow parameters be constant along the length of the volute. At off-design conditions the mismatching of characteristics causes variations of velocity and pressure along the periphery of the impeller. This in turn forces cyclic variation of the flow in the impeller channels, introduces variations of the inlet incidence and contributes significantly to the direction and the magnitude of the radial thrust. Furthermore, below a certain pump output, a complete flow reversal occurs over a part of the impeller periphery, thus explaining the onset of recirculation. The paper describes the calculation approach used to derive this aspect of the flow behavior. Because of difficulties in obtaining a closed analytical solution, a step by step computation is employed. Beginning with arbitrarily chosen conditions at the volute tongue, the program computes the flow parameters for following segments, using the continuity and the momentum equations, until the exit from the last segment is reached. The inherent unsteadiness of the relative flow in the impeller is explicitly accounted for. Since the inflow and the velocity in the first segment depend upon the exit conditions of the last, the initial input must be modified, and the computation repeated, until the values are compatible with the exit conditions. In spite of several simplifying assumptions, the results of the calculations show very good agreement with published test results.

Experimental Investigation of the Submarine Crashback Maneuver

2008 ◽  
Vol 130 (1) ◽  
Author(s):  
David H. Bridges ◽  
Martin J. Donnelly ◽  
Joel T. Park
Keyword(s):  
Vortex Structure ◽  
Thrust Force ◽  
Ring Vortex ◽  
Forward Motion ◽  
Compact Structure ◽  
Moment Coefficient ◽  
Different Types ◽  
Out Of Plane ◽  
Direction Opposite ◽  
Relative Flow

In order to decelerate a forward-moving submarine rapidly, often the propeller of the submarine is placed abruptly into reverse rotation, causing the propeller to generate a thrust force in the direction opposite to the submarine’s motion. This maneuver is known as the “crashback” maneuver. During crashback, the relative flow velocities in the vicinity of the propeller lead to the creation of a ring vortex around the propeller. This vortex has an unsteady asymmetry, which produces off-axis forces and moments on the propeller that are transmitted to the submarine. Tests were conducted in the William B. Morgan Large Cavitation Channel using an existing submarine model and propeller. A range of steady crashback conditions with fixed tunnel and propeller speeds was investigated. The dimensionless force and moment data were found to collapse well when plotted against the parameter η, which is defined as the ratio of the actual propeller speed to the propeller speed required for self-propulsion in forward motion. Unsteady crashback maneuvers were also investigated with two different types of simulations in which propeller and tunnel speeds were allowed to vary. It was noted during these simulations that the peak out-of-plane force and moment coefficient magnitudes in some cases exceeded those observed during the steady crashback measurements. Flow visualization and LDV studies showed that the ring vortex structure varied from an elongated vortex structure centered downstream of the propeller to a more compact structure that was located nearer the propeller as η became more negative, up to η=−0.8. For more negative values of η, the vortex core appeared to move out toward the propeller tip.

scholarly journals Numerical Investigation on the Influence of Hot Streak Temperature Ratio in a High-Pressure Stage of Vaneless Counter-Rotating Turbine

2007 ◽  
Vol 2007 ◽  
pp. 1-14 ◽  
Author(s):  
Zhao Qingjun ◽  
Wang Huishe ◽  
Zhao Xiaolu ◽  
Xu Jianzhong
Keyword(s):  
High Pressure ◽  
Secondary Flow ◽  
Heat Load ◽  
Rotor Blades ◽  
Inlet Temperature ◽  
Combined Effects ◽  
Temperature Ratio ◽  
Flow Angle ◽  
Hot Streak ◽  
Relative Flow

The results of recent studies have shown that combustor exit temperature distortion can cause excessive heat load of high-pressure turbine (HPT) rotor blades. The heating of HPT rotor blades can lead to thermal fatigue and degrade turbine performance. In order to explore the influence of hot streak temperature ratio on the temperature distributions of HPT airfoil surface, three-dimensional multiblade row unsteady Navier-Stokes simulations have been performed in a vaneless counter-rotating turbine (VCRT). The hot streak temperature ratios from 1.0 (without hot streak) to 2.4 were used in these numerical simulations, including 1.0, 1.2, 1.6, 2.0, and 2.4 temperature ratios. The hot streak is circular in shape with a diameter equal to 25%of the span. The center of the hot streak is located at 50%of span and 0%of pitch (the leading edge of the HPT stator vane). The predicted results show that the hot streak is relatively unaffected as it migrates through the HPT stator. The hot streak mixes with the vane wake and convects towards the pressure surface (PS) of the HPT rotor when it moves over the vane surface of the HPT stator. The heat load of the HPT rotor increases with the increase of the hot streak temperature ratio. The existence of the inlet temperature distortion induces a thin layer of cooler air in the HPT rotor, which separates the PS of the HPT rotor from the hotter fluid. The numerical results also indicating the migration characteristics of the hot streak in the HPT rotor are predominated by the combined effects of secondary flow and buoyancy. The combined effects that induce the high-temperature fluid migrate towards the hub on the HPT rotor. The effect of the secondary flow on the hotter fluid increases as the hot streak temperature ratio is increased. The influence of buoyancy is directly proportional to the hot streak temperature ratio. The predicted results show that the increase of the hot streak temperature ratio trends to increase the relative Mach number at the HPT rotor outlet, and decrease the relative flow angle from 25%to 75%span at the HPT rotor outlet. In the other region of the HPT outlet, the relative flow angle increases when the hot streak temperature ratio is increased. The predicted results also indicate that the isentropic efficiency of the VCRT decreases with the increase of the hot streak temperature ratio.

TCA cycle flux estimates from NMR- and GC-MS-determined [13C]glutamate isotopomers in liver

1997 ◽  
Vol 272 (6) ◽  
pp. C2049-C2062 ◽  
Author(s):  
J. A. Vogt ◽  
D. M. Yarmush ◽  
Y. M. Yu ◽  
C. Zupke ◽  
A. J. Fischman ◽  
...  
Keyword(s):  
Tca Cycle ◽  
Gas Chromatography Mass Spectrometry ◽  
Flow Rates ◽  
13C Nuclear Magnetic Resonance ◽  
Two Factors ◽  
Subsequent Measurement ◽  
System 1 ◽  
Relative Flow

Infusion of 13C-labeled lactate into rabbits and the subsequent measurement of glutamate isotopomers by 13C nuclear magnetic resonance (NMR) spectroscopy enables one to calculate relative flow rates associated with the tricarboxylic acid (TCA) cycle, albeit with a lower precision than one would obtain using a perfused organ. Two factors contribute to the lower precision in the determination of relative flow rates for the in vivo system: 1) a poorly defined pyruvate input and 2) low levels of 13C-enriched oxaloacetate and acetyl-CoA isotopomers, which give rise to weaker glutamate isotopomer NMR signals. To help overcome these limitations, we introduce a procedure to 1) include experimental data from gas chromatography-mass spectrometry (GC-MS) and 2) account for the uncertainty in the labeling of the input to pyruvate by creating the labeling as a measurement that is subject to measurement error. The effects of the uncertainties in the input labeling, NMR data, and MS data are evaluated via a Monte Carlo method. The change in the precision of the relative fluxes for the cases of high/low NMR and high/low MS precision is given. An uncertainty in the lactate measurements of up to 10% does not add significantly to the imprecision of the relative flow rates.

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