Review on thermal energy storage with phase change: materials, heat transfer analysis and applications

The boundary layer equations for plane, incompressible, and steady flow are 

$$\matrix{ {u{{\partial u} \over {\partial x}} + v{{\partial u} \over {\partial y}} = - {1 \over \varrho }{{\partial p} \over {\partial x}} + v{{{\partial ^2}u} \over {\partial {y^2}}},} \cr {0 = {{\partial p} \over {\partial y}},} \cr {{{\partial u} \over {\partial x}} + {{\partial v} \over {\partial y}} = 0.} \cr }$$

Boundary Layer Theory

An introduction to heat transfer

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Numerical Heat Transfer And Fluid Flow

This paper explores the recent research developments in high-heat-flux thermal management. Cooling schemes such as pool boiling, detachable heat sinks, channel flow boiling, microchannel and mini-channel heat sinks, jet-impingement, and sprays, are discussed and compared relative to heat dissipation potential, reliability, and packaging concerns. It is demonstrated that, while different cooling options can be tailored to the specific needs of individual applications, system considerations always play a paramount role in determining the most suitable cooling scheme. It is also shown that extensive fundamental electronic cooling knowledge has been amassed over the past two decades. Yet there is now a growing need for hardware innovations rather than perturbations to those fundamental studies. An example of these innovations is the cooling of military avionics, where research findings from the electronic cooling literature have made possible the development of a new generation of cooling hardware which promise order of magnitude increases in heat dissipation compared to today's cutting edge avionics cooling schemes.

Assessment of high-heat-flux thermal management schemes

Heat transfer—a review of 1995 literature

A bslruct-The governing equations for liquid and two-phase heat transfer are used to derive fluid figures of merit (FOM’s) for forced and natural convection, boiling incipience, and critical heal flux in both pool and flow boiling modes. These FOM’s can he used to evaluate and compare the thermal performance of several candidate immersion cooling fluids. In addition, the governing equations are used to determine the sensitivities of thermal performance to fluid property values.

/pdf/fluid-selection-and-property-effects-in-single-and-two-phase-2ml4pizztj.pdf

Fluid Selection and Property Effects in Single- and Two-Phase Immersion Cooling

To date, very little attention has been devoted to the scales and turbulence energy spectra of coolant exiting from film cooling holes. Length-scale documentation and spectral measurements have primarily been concerned with the free-stream flow with which the coolant interacts. Documentation of scales and energy decomposition of the coolant flow leads to more complete understanding of this important flow and the mechanisms by which it disperses and mixes with the free stream. CFD modeling of the emerging flow can use these data as verification that flow computations are accurate. To address this need, spectral measurements were taken with single-sensor, hot-wire anemometry at the exit plane of film cooling holes. Energy spectral distributions and length scales calculated from these distributions are presented for film cooling holes of different lengths and for coolant supply plenums of different geometries. Measurements are presented on the hole streamwise centerline at the center of the hole, one-half diameter upstream of center, and one-half diameter downstream of center. The data highlight some fundamental differences in energy content, dominant frequencies, and scales with changes in the hole and plenum geometries. Coolant flowing through long holes exhibits smoothly distributed spectra as might be anticipated in fully developed tube flows. Spectra from short-hole flows, however, show dominant frequencies.

/pdf/turbulence-spectra-and-length-scales-measured-in-film-2o5hgbpe59.pdf

Turbulence Spectra and Length Scales Measured in Film Coolant Flows Emerging From Discrete Holes

The SR-30 is a small-scale, turbojet engine which sounds and smells like a real engine used to fly commercial aircraft. With an overall length of less than 2.0 feet and an average diameter of 6.5 inches, the SR-30 is equipped with an inlet nozzle, radial compressor, counter-flow combustion chamber, turbine, and exhaust nozzle. Although it can operate on various fuels, diesel fuel is used in the studies described here, and each component is instrumented with thermocouples and pressure gages to allow a complete thermodynamic evaluation. Screaming along at 80,000 rpm and sending out exhaust gas at 500 mph, the SR-30 engine is fun science for students! However, since the SR-30 was essentially designed for one-dimensional measurement and flow analysis, students quickly learn the limitations of these assumptions.

Terrence W. Simon

Papers

Heat transfer—a review of 1995 literature

Fluid Selection and Property Effects in Single- and Two-Phase Immersion Cooling

Turbulence Spectra and Length Scales Measured in Film Coolant Flows Emerging From Discrete Holes

Characterizing the performance of the sr-30 turbojet engine

Heat transfer from a small, high-heat-flux patch to a subcooled turbulent flow.