Measurement of temperature profile near the evaporating interface in an annular pool with radial temperature gradients at low pressures

2020 ◽  
Vol 119 ◽  
pp. 110221
Author(s):  
Rui-Feng Guo ◽  
Li Zhang ◽  
Dong-Ming Mo ◽  
Chun-Mei Wu ◽  
You-Rong Li
Keyword(s):  
Temperature Profile ◽  
Temperature Gradients ◽  
Radial Temperature ◽  
Annular Pool ◽  
Low Pressures

scholarly journals Unsteady Numerical Simulations of Radial Temperature Profile Redistribution in a Single-Stage Turbine

1995 ◽  
Author(s):  
Daniel J. Dorney ◽  
John R. Schwab
Keyword(s):  
Experimental Data ◽  
Temperature Profile ◽  
Total Pressure ◽  
Three Dimensional ◽  
Temperature Gradients ◽  
Single Stage ◽  
Angle Distribution ◽  
Pressure Gradients ◽  
Flow Angle ◽  
Radial Temperature

Experimental data taken from gas turbine combustors indicate that the flow exiting the combustor can contain both circumferential and radial temperature gradients. A significant amount of research recently has been devoted to studying turbine flows with inlet temperature gradients, but no total pressure gradients. Less attention has been given to flows containing both temperature and total pressure gradients at the inlet. The significance of the total pressure gradients is that the secondary flows and the temperature redistribution process in the vane blade row can be significantly altered. Experimental data previously obtained in a single-stage turbine with inlet total temperature and total pressure gradients indicated a redistribution of the warmer fluid to the pressure surface of the airfoils, and a severe underturning of the flow at the exit of the stage. In a concurrent numerical simulation, a steady, inviscid, three-dimensional flow analysis was able to capture the redistribution process, but not the exit flow angle distribution. In the current research program, a series of unsteady two- and three-dimensional Navier-Stokes simulations have been performed to study the redistribution of the radial temperature profile in the turbine stage. The three-dimensional analysis predicts both the temperature redistribution and the flow underturning observed in the experiments.

Transient Heat Transfer in a Packed-Bed Elliptic Cylindrical Reactor: A Finite-Volume Approach

2017 ◽  
Vol 380 ◽  
pp. 79-85 ◽  
Author(s):  
R. Moura da Silva ◽  
A.G. Barbosa de Lima ◽  
L. Gomes de Oliveira ◽  
Morgana Vasconcellos Araújo ◽  
R.S. Santos
Keyword(s):  
Heat Transfer ◽  
Temperature Profile ◽  
Heat Transfer Rate ◽  
Finite Volume ◽  
Transfer Rate ◽  
Temperature Gradients ◽  
Fixed Bed Reactor ◽  
Radial Temperature ◽  
Maximum Heat ◽  
Reactor Surface

This work aims to develop a transient three-dimensional mathematical model using the elliptic cylindrical coordinate system, to predict heat transfer in a elliptic cylindrical packed fixed bed reactor. The model considers variable thermo physical properties and a parabolic temperature profile at the fluid inlet. The governing equation is solved using the finite volume method. Results of temperature profile along the reactor are presented and discussed at different moments.It was verified that the maximum heat transfer rate inside the reactor occurs near the extreme region close to minor semi-axis of the ellipse; the higher temperatures at the reactor surface are also in this region, along the entire height of the bed; the steady-state regime is reached at t = 4.5 s of process, presenting after this time interval,small axial temperature gradients and high radial gradients along of the reactor bed; the parabolic temperature profile give to the bed a predominance of radial temperature gradients, and the radial porosity profile favours a higher heat transfer rate at reactor surface.

Unsteady Numerical Simulations of Radial Temperature Profile Redistribution in a Single-Stage Turbine

1996 ◽  
Vol 118 (4) ◽  
pp. 783-791 ◽  
Author(s):  
D. J. Dorney ◽  
J. R. Schwab
Keyword(s):  
Experimental Data ◽  
Temperature Profile ◽  
Total Pressure ◽  
Three Dimensional ◽  
Temperature Gradients ◽  
Single Stage ◽  
Angle Distribution ◽  
Pressure Gradients ◽  
Flow Angle ◽  
Radial Temperature

Experimental data taken from gas turbine combustors indicate that the flow exiting the combustor can contain both circumferential and radial temperature gradients. A significant amount of research recently has been devoted to studying turbine flows with inlet temperature gradients, but no total pressure gradients. Less attention has been given to flows containing both temperature and total pressure gradients at the inlet. The significance of the total pressure gradients is that the secondary flows and the temperature redistribution process in the vane blade row can be significantly altered. Experimental data previously obtained in a single-stage turbine with inlet total temperature and total pressure gradients indicated a redistribution of the warmer fluid to the pressure surface of the airfoils, and a severe underturning of the flow at the exit of the stage. In a concurrent numerical simulation, a steady, inviscid, three-dimensional flow angle distribution, In the current research program, a series of unsteady two-and three-dimensional Navier–Stokes simulations have been performed to study the redistribution of the radial temperature profile in the turbine stage. The three-dimensional analysis predicts both the temperature redistribution and the flow underturning observed in the experiments.

scholarly journals A Method for Determining the Main Requirements of Outlet Gas Temperature Profile of Marine Gas Turbine Combustors

1982 ◽  
Author(s):  
Tang Chian-ti
Keyword(s):  
Temperature Distribution ◽  
Temperature Profile ◽  
Gas Turbine ◽  
Guide Vane ◽  
Safety Margin ◽  
Gas Temperature ◽  
Distribution Factor ◽  
Radial Temperature ◽  
Blade Height ◽  
Blade Cooling

Taking account of the marine gas turbine operation features, the author has chosen the hot corrosion peak temperature of materials as the guide vane material limiting temperature while evaluating the overall temperature distribution factor. Along with the blade cooling effectiveness a safety margin factor has been introduced during its evaluation. The gas temperature distribution along blade height is assumed to satisfy the condition that approximately equal safety factor in respect of strength prevails along blade height. Once the gas radial temperature profile becomes known, the radial temperature distribution factor can be readily determined.

A new method of determining the transport coefficients for high pressure arcs from experimental data

1969 ◽  
Vol 3 (2) ◽  
pp. 269-280 ◽  
Author(s):  
L. B. Kapp ◽  
P. H. Richards
Keyword(s):  
Experimental Data ◽  
High Pressure ◽  
Computer Program ◽  
Numerical Method ◽  
Temperature Profile ◽  
Transport Coefficients ◽  
New Method ◽  
Radial Temperature ◽  
Current Voltage ◽  
Current Voltage Characteristics

The problem is to determine the electrical and thermal conductivities of high pressure are plasmas from measurements of the current—voltage characteristics of the are and a single radial temperature profile. A new numerical method is described together with the corresponding computer program. The latter is applied to some recent measurements on wall-stabilized nitrogen ares, covering the temperature range 4500—11,000 °K, for which radiation can be neglected, and the results are compared with those of other workers.

Modeling of Thermal Stresses and Thermal Cracking During Heating of Large Ingots

1996 ◽  
Vol 118 (2) ◽  
pp. 235-243 ◽  
Author(s):  
M. K. Alam ◽  
R. L. Goetz ◽  
S. L. Semiatin
Keyword(s):  
Thermal Stresses ◽  
Titanium Aluminides ◽  
Temperature Gradients ◽  
End Effects ◽  
Radial Temperature ◽  
Stress Criterion ◽  
Intermetallic Materials ◽  
Analytical Series ◽  
Biot Numbers ◽  
Selection Of

The development of temperature gradients and thermal stresses during the heating of large ingots has been investigated with special reference to the selection of heating schedules for brittle intermetallic materials such as titanium aluminides. A 1-D analytical (series) solution for radial temperature transients was used in conjunction with an elasticity analysis to determine the maximum thermal stresses that would be generated during ingot heating. The temperature gradients and stresses were seen to be strongly dependent on Fourier and Biot Numbers. In addition, finite element method simulations incorporating end effects and variations of thermal and elastic properties with temperature were performed and compared to the analytical results. Comparison of the predicated thermal stresses and actual ingot heating observations suggest that cracking is controlled by a maximum normal stress criterion.

A NUMERICAL INVESTIGATION OF THE FLOW IN A FULLY BLOCKED DIFFERENTIALLY HEATED ROTATING FLUID ANNULUS

1994 ◽  
Vol 05 (02) ◽  
pp. 203-206 ◽  
Author(s):  
Q.G. RAYER
Keyword(s):  
Computational Model ◽  
Horizontal Plane ◽  
Computer Modelling ◽  
Temperature Gradients ◽  
Rotating Fluid ◽  
Dynamical Equations ◽  
Radial Temperature ◽  
Rotation Rates ◽  
Horizontal Circulation ◽  
Simply Connected

A computational model has been used to determine the terms in the dynamical equations which are responsible for the formation of a certain horizontal circulation seen in a simply connected, differentially heated rotating fluid annulus. Experiments with a differentially heated rotating fluid annulus that is fully blocked by a thin, rigid, vertical radial barrier at rotation rates of up to 5 rad.sec−1 and with an externally applied radial temperature difference of 4 or 10 °C show two principal circulations. This paper is concerned with the mechanism for one of those circulations, which occurs in a horizontal plane. Computer modelling shows that this circulation is caused by small radial temperature gradients in the fluid, rather than centrifugal effects.

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