Multidimensional Assessment of Modeling Error in Typical High-Speed Wind-Tunnel Heat-Transfer Data-Reduction Schemes

2009 ◽  
Vol 23 (1) ◽  
pp. 186-191 ◽  
Author(s):  
Benjamin S. Kirk
Author(s):  
Susan N. Ritchey

Shell-and-tube vacuum condensers are present in many industrial applications such as chemical manufacturing, distillation, and power production [1–3]. They are often used because operating a condenser under vacuum pressures can increase the efficiency of energy conversion, which increases the overall plant efficiency and saves money. Typical operating pressures in the petrochemical industry span a wide range of values, from one atmosphere (101.3 kPa) down to a medium vacuum (1 kPa). The current shellside condensation methods used to predict heat transfer coefficients are based on data collected near or above atmospheric pressure, and the available literature on shellside vacuum condensation generally lacks experimental data. The accuracy of these methods in vacuum conditions well below atmospheric pressure has yet to be validated. Recently, HTRI designed and constructed the Low Pressure Condensation Unit (LPCU) with a rectangular shellside test condenser. To date, heat transfer data have been collected in the LPCU for shellside condensation of a pure hydrocarbon and of a hydrocarbon with noncondensable gas at vacuum pressures ranging from 2.8 to 45 kPa (21 to 338 Torr). Traditional condensation literature methods underpredict the overall heat transfer coefficient by 20.8% ± 20.4% for the pure condensing fluid; whereas they overpredict heat transfer by 36.8% ± 40.0% with the addition of the noncondensable gas. Over or under predicting the overall heat transfer coefficient in the presence of noncondensable gases leads to inefficient condenser designs and the inability to achieve desired process conditions. With the addition of the noncondensable gas, the measured heat exchanger duty was significantly reduced compared to the pure fluid, even at inlet mole fractions below 5%. In one case, a noncondensable inlet mole fraction of 0.63% was estimated to reduce the duty by approximately 10%. Analysis of the acquired high-speed videos shows that the film thickness changes significantly from the top row to the bottom. The videos also display condensate drainage patterns and droplet interactions. The ripples and splashing of the condensate observed in the videos indicates that the Nusselt idealized model is not appropriate for analysis of a real condenser. This article presents the collected heat transfer data and high-speed images of shellside vacuum condensation flow patterns.


Author(s):  
Nitesh D. Nimkar ◽  
Sushil H. Bhavnani ◽  
Richard C. Jaeger

Pool boiling from a surface featuring micro-pyramidal re-entrant cavities (mouth size 40 μm) etched in silicon, on a glass substrate, was studied. All experiments were conducted in the dielectric fluid FC-72 at one atmosphere. The heat sink is designed to eliminate spreading through the substrate, and back heat loss. Experimentation showed that the critical heat flux was 12.8 W/cm2. A high speed camera (400fps) was used to record and quantify the effect of heat flux on departure diameter and bubble emission frequency. Both departure diameter and frequency showed an increasing trend with heat flux. Comparison with existing literature are also presented.


As automation and mechanical industry growing towards next era, it becoming crucial to design each element of plant with more productive material. Out of many parameters, heat transfer is very important area of study to lower the rate of failure of numerous machines. For heat transfer control there is a need of design of efficient heat exchanger. A heat exchanger can be designed for minimization of heat energy from the wind tunnel. Impact on HE performance is important due to the thermal resistance of wind tunnel. Thermal resistance is the heat property of the tunnel material and dimensions of tunnel. Looking at application level performance, the thermal resistance is crucial element in case of aerodynamic study. The similar study is done for Apolo11 spacecraft which was important in case of landing back to earth as traveling to earth with high speed generated heat which can damage spacecraft body. Such study further leads to various domains like material research, human impact study etc. The most recently, asteroid is passed nearby of earth orbit, where aerodynamic study of NASA evaluated the pre-collision effects where thermal properties are analyzed considering the atmospheric nearby orbit as a tunnel of wind/pressure. Hence, the scenarios must be considered for heat transfer / heat exchanger design specific to the each application domain. This paper discusses about the asteroid bypass which generates heat as a major heat transfer to earth and the automobile specific modeling of heat exchanger for wind tunnel. The focus is kept on heat exchanger design which can be suggested for automobile testing procedure.


1981 ◽  
Vol 103 (4) ◽  
pp. 678-687 ◽  
Author(s):  
M. F. Blair ◽  
D. A. Bailey ◽  
R. H. Schlinker

The procedures employed for the design of a closed-circuit, boundary layer wind tunnel are described. The tunnel was designed for the generation of large-scale, two-dimensional boundary layers on a heated flat surface with Reynolds numbers, pressure gradients, and free-stream turbulence levels typical of turbomachinery airfoils. The results of a series of detailed tests to evaluate the tunnel performance are also described. Testing was conducted for zero pressure gradient flow with natural boundary layer transition. Heat transfer data and boundary layer profiles are presented for a flow with 0.25 percent free-stream turbulence. The flow in the tunnel test-section was shown to be highly uniform and two-dimensional. Test boundary layer profile and convective heat transfer data were self-consistent and in excellent agreement with classic correlations. Test-section free-stream total pressure, multi-component turbulence intensity, longitudinal integral scale, and spectral distributions are presented for grid-generated turbulence levels ranging from 1 to 7 percent. The test-section free-stream turbulence was shown to be both homogeneous and nearly isotropic. Anticipated applications of the facility include studies of the heat transfer and aerodynamics for conditions typical of those existing on gas turbine airfoils.


2020 ◽  
Vol 34 (4) ◽  
pp. 860-864
Author(s):  
J. I. Frankel ◽  
Rowland T. Penty Geraets ◽  
M. McGilvray ◽  
Hongchu Chen

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