Investigation of heat transfer mechanism of low environmental pressure large-space spray cooling for near-space flight systems

Wang, Ji‐Xiang; Li, Yunze; Yu, Xi-Kui; Li, Guangchao; Ji, Xin-Yan

doi:10.1016/j.ijheatmasstransfer.2017.11.128

Cited by 72 publications

(17 citation statements)

References 36 publications

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“…In order to generalize the heat transfer laws of spray cooling deduced from the experimental data and enlighten the future application of the novel cooling technology, further data process, and experimental dimensionless study has been organized. Since the flow diffusion in the current condition where the air is applied, the Knudsen number Kn [41] is a critical parameter to implement the full-scale application and criteria to choose the correct models to describe the spray flow state as well. Kn is defined by Equation (7) where κ is the mean free path of the molecule which can be calculated by Equation (8) and the parameter D is characteristic length of the experimental surface which is equal to value of the equivalent hydraulic diameter.…”

Section: Experimental Dimensionless Correlationmentioning

confidence: 99%

“…Except for the effect of gravity, the environmental pressure (EP) also is a highlight trait in the aerospace in which the spray parameters may be changed due to the PD between the nozzle inlet pressure and the surrounding one. In addition, the heat transfer could be enhanced because of the flash boiling, bringing about an improved thermal transfer performance when the surrounding pressure is lower than the saturation pressure of the coolant [41]. The heat transfer performance influenced by low EP, which range is 0.2-0.4 MPa, was researched by Liu et al [42].…”

Section: Introductionmentioning

confidence: 99%

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Experimental Investigation on Heat Transfer Mechanism of Air-Blast-Spray-Cooling System with a Two-Phase Ejector Loop for Aeronautical Application

Cai

et al. 2019

Energies

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This paper presents an air-oriented spray cooling system (SCS) integrated with a two-phase ejector for the thermal management system. Considering its aeronautical application, the spray nozzle in the SCS is an air-blast one. Heat transfer performance (HTP) of air-water spray cooling was studied experimentally on the basis of the ground-based test. Factors including pressure difference between water-inlet-pressure (WIP) and spray cavity one (PDWIC) and the spray volumetric flow rate (SVFR) were investigated and discussed. Under a constant operating condition, the cooling capacity can be promoted by the growth factors of the PDWIC and SVFR with the values from 51.90 kPa to 235.35 kPa and 3.91 L ⋅ h − 1 to 14.53 L ⋅ h − 1 , respectively. Under the same heating power, HTP is proportional to the two dimensionless parameters Reynolds number and Weber number due to the growth of droplet-impacting velocity and droplet size as the increasing of PDWIC or SVFR. Additionally, compared with the factor of the droplet size, the HTP is more sensitive to the variation in the droplet-impacting velocity. Based on the experimental data, an empirical experimental correlation for the prediction of the dimensionless parameter Nusselt number in the non-boiling region with the relative error of only ± 10 % was obtained based on the least square method.

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Section: Experimental Dimensionless Correlationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Heat Transfer Mechanism of Air-Blast-Spray-Cooling System with a Two-Phase Ejector Loop for Aeronautical Application

Cai

et al. 2019

Energies

Self Cite

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“…In general, typical cooling techniques for electric machine applications are based on air cooling systems [9][10][11], phase-change material cooling systems [12,13] and liquid cooling systems [14][15][16][17][18]. Because liquids have a higher heat transfer capacity than air of the same mass, in applications where there is a large amount of heat generated continuously, the liquid cooling systems are more suitable than air cooling systems in terms of heat transfer performance and size of the cooling system.…”

Section: Introductionmentioning

confidence: 99%

On Heat Transfer Performance of Cooling Systems Using Nanofluid for Electric Motor Applications

Deriszadeh

Monte

2020

Entropy

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This paper studies the fluid flow and heat transfer characteristics of nanofluids as advance coolants for the cooling system of electric motors. Investigations are carried out using numerical analysis for a cooling system with spiral channels. To solve the governing equations, computational fluid dynamics and 3D fluid motion analysis are used. The base fluid is water with a laminar flow. The fluid Reynolds number and turn-number of spiral channels are evaluation parameters. The effect of nanoparticles volume fraction in the base fluid on the heat transfer performance of the cooling system is studied. Increasing the volume fraction of nanoparticles leads to improving the heat transfer performance of the cooling system. On the other hand, a high-volume fraction of the nanofluid increases the pressure drop of the coolant fluid and increases the required pumping power. This paper aims at finding a trade-off between effective parameters by studying both fluid flow and heat transfer characteristics of the nanofluid.

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“…Besides, several advanced heat transfer methods of TMS have also been proposed. Wang et al [35][36][37] investigated the flash boiling spray cooling under the high altitude condition (low ambient pressure), which shows excellent heat dissipation ability for extreme heat flux devices. Deng [38] and Ma [39] have investigated the mini-channel heat sink numerically and experimentally, showing good performance for the application in the cooling of high heat flux microelectronic devices.…”

Section: Introductionmentioning

confidence: 99%

Cooling Ability/Capacity and Exergy Penalty Analysis of Each Heat Sink of Modern Supersonic Aircraft

Mao

Wang

et al. 2019

Entropy

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The aerospace-based heat sink is defined as a substance used for dissipating heat generated by onboard heat loads. They are becoming increasingly scarce in the thermal management system (TMS) of advanced aircraft, especially for supersonic aircraft. In the modern aircraft there are many types of heat sinks whose cooling abilities and performance penalties are usually obviously different from each other. Besides, the cooling ability and performance penalty of a single heat sink is even different under different flight conditions—flight altitude, Mach number, etc. In this study, the typical heat sinks which are the fuel mass, ram air, engine fan air, skin heat exchanger, and expendable heat sink will be studied. Their cooling abilities/capacities, and exergy penalties under different flight conditions have been systematically estimated and compared with each other. The exergy penalty presented in this paper refers to the exergy loss of aircraft caused by the extra weight, drag and energy extraction of various heat sinks. The estimation models, as well as the results and discussion have been elaborated in this paper, which can be can be used to further optimize the TMS of modern advanced aircraft, for example, the layout design of various heat sinks and the improvement the control algorithm.

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Investigation of heat transfer mechanism of low environmental pressure large-space spray cooling for near-space flight systems

Cited by 72 publications

References 36 publications

Experimental Investigation on Heat Transfer Mechanism of Air-Blast-Spray-Cooling System with a Two-Phase Ejector Loop for Aeronautical Application

Experimental Investigation on Heat Transfer Mechanism of Air-Blast-Spray-Cooling System with a Two-Phase Ejector Loop for Aeronautical Application

On Heat Transfer Performance of Cooling Systems Using Nanofluid for Electric Motor Applications

Cooling Ability/Capacity and Exergy Penalty Analysis of Each Heat Sink of Modern Supersonic Aircraft

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