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

In modern gas turbines, film cooling technology is the most common and efficient way to provide thermal protection for hot parts. To improve film cooling effectiveness, different kinds of shaped holes have been designed, but most of them are complicated and difficult to machine. In this study, four cases of novel film cooling hole design, all based on cylindrical holes, are numerically studied. One is a single, two-stage cylindrical hole, whose downstreamhalf-length has a diameter D while the upstreamhalf-length has a diameter D/2. A second has a cylindrical primary hole with two smaller secondary holes located symmetrically about the centerline of the primary hole and downstream of the primary hole. The three holes of this second design are then combined to make a single shaped hole, constituting a third case, called the tri-circular shaped hole. The entry part of the third case is replaced by a cylindrical hole with a diameter of half the primary hole diameter, making a fourth case called the two-stage tri-circular shaped hole. Film cooling effectiveness and surrounding thermal and flow fields are numerically investigated for all four cases using various blowing ratios. It is shown from the simulation that the two-stage cylindrical hole cannot improve film cooling effectiveness. The primary hole with two secondary holes can enhance film cooling performance by creating anti-kidney vortex pairs, which will weaken jet lift-off, caused by the kidney vortex pairs, from the primary hole. The tri-circular shaped hole will provide better film cooling effectiveness near the hole area, and is not sensitive to blowing ratio. The two-stage structure for tri-circular shaped hole provides better film coverage because it changes the flow structure inside the channel and decreases jet penetration.Copyright © 2018 by ASME

New Designs of Novel Holes Based on Cylindrical Configurations for Improving Film Cooling Effectiveness

Heat transfer—a review of 1990 literature

Free-stream turbulence effects on convexly curved turbulent boundary layers.

Gas turbine heat transfer

The high pressure turbine stage possesses a wealth of complexities for designers to consider. One of recent interest is that of leakage (or purge) flow ejection at the stator-to-rotor interface. At this interface, a small cavity is designed into the engine to provide clearance between the rotor disk and the stator. The dimensions of this cavity can vary as a result of transient operating conditions. The ideal cavity is as small as practical. The cavity must be protected from hot gas ingression. Current designs meter flow bled from the high pressure compressor into the cavity using labyrinth seals, as shown in Figure 1. This flow, used to prevent ingression of hot gas from the passage, also offers cooling. Its interaction with the hot gas path flow as it exits the disc cavity, is the topic of this study.

Terrence W. Simon

Papers

New Designs of Novel Holes Based on Cylindrical Configurations for Improving Film Cooling Effectiveness

Heat transfer—a review of 1990 literature

Free-stream turbulence effects on convexly curved turbulent boundary layers.

Gas turbine heat transfer

Effects of stator/rotor leakage flow and axisymmetric contouring on endwall adiabatic effectiveness and aerodynamic loss