Thesis (M. App. Sc.) -- University of Adelaide, Department of Chemical Engineering, 1973.

The impact of thermal stress on psychological performance has been the subject of considerable research attention. However, the effects of heat on performance are poorly understood. The literature yields inconsistent results, reflecting methodological shortcomings in previous research, particularly with regard to the definition of the independent variable. Investigators have focused on heat stress per se to the neglect of the participants' thermal physiological response. In addition, investigators have typically tested small samples, and have relied on a limited range of performance measures of unknown sensitivity. Few theoretical accounts of performance during thermal stress have been proposed, and these are poorly elaborated. The principal aim of this research programme was to elucidate the effects of heat on psychological performance. Emphasis was placed on defining the independent variable in terms of physiological strain. Performance was measured using a comprehensive range of sensitive tasks. In the first and second experiments, an innovative water immersion technique was used to control thermal strain precisely. The principal effect of heat strain observed in these experiments was an increase in the speed of performance, without variation in accuracy. This effect was attributed to an increase in nerve conduction velocity associated with raised body temperature. The duration of immersion in the second experiment was fifty percent longer than that in the first, but little variation in performance with the duration of heat strain was evident. In light of the limited external validity of the immersion experiments, subsequent investigation focused on the effects of more realistic sources of thermal strain. A survey of military personnel indicated that occupational exposure to thermal stress is perceived to impair some cognitive and psychomotor functions. The final experiment measured performance during prolonged exposure to heat stress in a climatic chamber. The results indicate that the performance changes observed in the immersion experiments generalize to conditions involving exposure to more realistic sources of heat strain

Approved for public release; distribution is unlimited / Heat-transfer measurements were made for condensation of R-113 and steam on a smooth tube and on three finned tubes with rectangular shape fins. These tubes had a fin height and width of 1.0 mm and spacings of 0.25, 1.5, and 4.0 mm (tubes A, B, and C respectively) . Data were taken by increasing the vapor velocity from 0.4 to 1.9 m/s for R-113 and 4.8 to 31.3 m/s for steam. For both fluids, the improvement of the condensing heat-transfer coefficient with vapor velocity was smaller for the finned tubes than for the smooth tube. For R-113, the smooth tube experienced a 32 percent improvement with vapor velocity, where the finned tubes (tubes A, B and C respectively) experienced improvements of only 0, 5 and 10 percent. For steam, the smooth tube experienced a 62 percent improvement, whereas the finned tubes (tubes A, B, and C respectively) experienced improvements of only 31, 11, and 9 percent. These test results show that, although finned tubes can provide significant heat transfer enhancement over smooth tubes at low vapor velocities, the degree of enhancement becomes smaller as vapor velocity increases. / CBT-8603582 (NSF) / http://archive.org/details/effectofvaporvel00hopk / National Science Foundation / Lieutenant Commander, United States Navy

O modelo de avaliação da camada limite dinâmica e térmica foi implementado, no presente trabalho, em um código numérico para o cálculo do coeficiente de transferência de calor convectivo sobre aerofólios de uso aeronáutico com formação de gelo. Foram considerados, no modelo da camada limite turbulenta, os efeitos da rugosidade equivalente do grão de areia ks, e transição entre o regime laminar e turbulento foi avaliada por dois modelos, um abrupto e um suave. Para a transição suave foi utilizada uma função intermitência proposta por (ABU-GHANNAM; SHAW, 1980). O código desenvolvido neste trabalho foi acoplado aos módulos do código ONERA com o objetivo de simular as formas de gelo em aerofólios para diversas condições de escoamento do ar com conteúdo de água. As formas de gelo obtidas foram comparadas com dados experimentais de Shine Bond (1994) e com resultados de simulações dos códigos LEWICE, TRAJICE e ONERA (KIND, 2001). Os resultados das simulações do presente trabalho apresentaram boa semelhança com os resultados dos outros códigos. A simulação da previsão de formas de gelo do tipo Glaze, do presente trabalho e dos outros códigos, resultou em formas de gelo de espessura e volume menores que as formas experimentais. Foi verificado que uma previsão adequada do coeficiente de transferência de calor convectivo afeta a simulação das formas deste tipo de gelo. Um caso de Kind (2001) foi utilizado para avaliar os efeitos dos parâmetros da camada limite dinâmica e térmica na formação de gelo em aerofólios. Verificou-se que a posição do início da transição do regime laminar para o turbulento, o comprimento d a transição e o valor da rugosidade afetam a forma, a espessura e o volume do gelo, e que estes parâmetros podem ser utilizados para ajustes dos modelos de camada limite para melhores previsões de formas de gelo do tipo Glaze. / The model to evaluate the momentum and thermal boundary layer was implemented, in the present work, in a numerical module to calculate the convective heat transfer coecient over aeronautical airfoils with ice accretion. It was considered, in the turbulent boundary layer model, the eects of the equivalent sand grain roughness ks , and the laminar to turbulent transition was evaluated with two models, the abrupt and the smooth one. The smooth transition model used an intermittency function proposed by (ABU-GHANNAM; SHAW, 1980). The module developed in this work was integrated with the modules of the code ONERA in order to simulate the airfoil icing shapes for several air stream with water droplets condition. The ice shapes obtained was compared with experimental data of Shin e Bond (1994) and with simulation results for the codes LEWICE, TRAJICE e ONERA (KIND, 2001). The results of the simulations for the present work showed a good similarity with the other codes results. The Glaze icing shapes simulation, in the present work and in the other codes, resulted in icing shapes with thickness and volumes lesser than the experimental shapes. It was noted that a reasonable prediction of the convective heat transfer coecient aects the simulation of this type of ice shape. One case of Kind (2001) was used to evaluate the eects of the momentum and thermal boundary layer for the icing accreations in the airfoil. It was noted the onset position, the lenght of the laminar-turbulent transition, and the sand grain roughness value aects the icing shape, thickness and volume and this parameters might be used to adjust the boundary layer models in order to get better predictions of Glaze icing shapes.

Six elite wheelchair shooters undertook a simulated competition of 2 hr duration under three different conditions: 1. 24-26 °C and 40% humidity (C), 2. 36 °C and 60% humidity (H), and 3. the H condition whilst using simple head, neck and torso cooling devices (HC). The trials were undertaken at the same time on consecutive days in a counter-balanced, randomised order. Two shooters were removed from the H trial at t=75 and t=105 min, respectively, due to tympanic temperature elevations above 39 °C, but were able to complete the full 2 hr of competition during the C and HC conditions. Heart rates were significantly elevated for the group during the H condition compared to C and HC (106 ± ll, 80 ± 10, 90 ± 7 beats.min-' respectively at t=90 min, p<0.05) as were perceptions of thermal discomfort (6.4 ± 0.7, 3.5 ± 0.4, 4.8 ± 1.0 respectively at t=90 min, p<0.05). These responses were at least partially alleviated by the use of the simple, yet practical, cooling devices. Practically, this may improve performance in shooting competitions as it allows more time to fire a shot between heart beats, and enables shooters to concentrate more easily on the task required of them. Responses to heat exposure were more pronounced in athletes with a higher level of disability (CS versus T4 versus cerebral palsy), and those who wore heavy leather shooting jackets (rifle versus pistol shooters). Although further research is recommended, it would appear that the rules governing shooting attire and prolonging exposure to heat should be reconsidered for events in which wheelchair athletes compete.

O modelo de avaliação da camada limite dinâmica e térmica foi implementado, no presente trabalho, em um código numérico para o cálculo do coeficiente de transferência de calor convectivo sobre aerofólios de uso aeronáutico com formação de gelo. Foram considerados, no modelo da camada limite turbulenta, os efeitos da rugosidade equivalente do grão de areia ks, e transição entre o regime laminar e turbulento foi avaliada por dois modelos, um abrupto e um suave. Para a transição suave foi utilizada uma função intermitência proposta por (ABU-GHANNAM; SHAW, 1980). O código desenvolvido neste trabalho foi acoplado aos módulos do código ONERA com o objetivo de simular as formas de gelo em aerofólios para diversas condições de escoamento do ar com conteúdo de água. As formas de gelo obtidas foram comparadas com dados experimentais de Shine Bond (1994) e com resultados de simulações dos códigos LEWICE, TRAJICE e ONERA (KIND, 2001). Os resultados das simulações do presente trabalho apresentaram boa semelhança com os resultados dos outros códigos. A simulação da previsão de formas de gelo do tipo Glaze, do presente trabalho e dos outros códigos, resultou em formas de gelo de espessura e volume menores que as formas experimentais. Foi verificado que uma previsão adequada do coeficiente de transferência de calor convectivo afeta a simulação das formas deste tipo de gelo. Um caso de Kind (2001) foi utilizado para avaliar os efeitos dos parâmetros da camada limite dinâmica e térmica na formação de gelo em aerofólios. Verificou-se que a posição do início da transição do regime laminar para o turbulento, o comprimento d a transição e o valor da rugosidade afetam a forma, a espessura e o volume do gelo, e que estes parâmetros podem ser utilizados para ajustes dos modelos de camada limite para melhores previsões de formas de gelo do tipo Glaze. / The model to evaluate the momentum and thermal boundary layer was implemented, in the present work, in a numerical module to calculate the convective heat transfer coecient over aeronautical airfoils with ice accretion. It was considered, in the turbulent boundary layer model, the eects of the equivalent sand grain roughness ks , and the laminar to turbulent transition was evaluated with two models, the abrupt and the smooth one. The smooth transition model used an intermittency function proposed by (ABU-GHANNAM; SHAW, 1980). The module developed in this work was integrated with the modules of the code ONERA in order to simulate the airfoil icing shapes for several air stream with water droplets condition. The ice shapes obtained was compared with experimental data of Shin e Bond (1994) and with simulation results for the codes LEWICE, TRAJICE e ONERA (KIND, 2001). The results of the simulations for the present work showed a good similarity with the other codes results. The Glaze icing shapes simulation, in the present work and in the other codes, resulted in icing shapes with thickness and volumes lesser than the experimental shapes. It was noted that a reasonable prediction of the convective heat transfer coecient aects the simulation of this type of ice shape. One case of Kind (2001) was used to evaluate the eects of the momentum and thermal boundary layer for the icing accreations in the airfoil. It was noted the onset position, the lenght of the laminar-turbulent transition, and the sand grain roughness value aects the icing shape, thickness and volume and this parameters might be used to adjust the boundary layer models in order to get better predictions of Glaze icing shapes.

No description available.

Additive manufacturing (AM) has largely improved design freedom compared with traditional manufacturing processes such as casting and milling. The layer-by-layer workflow makes it possible to produce objects with much more complex shapes and structures. This feature is of particular interest for turbine blade manufacturing since internal cooling channels with higher thermal efficiency can be achieved toimprove the overall efficiency of a gas turbine. One feature of AM, especially for Laser Power Bed Fusion (LPBF) working on metal powders, is the relatively large surface roughness (SR), which will affect both heat transfer and pressure loss. Its geometry is also unique with the very randomly distributed spherical-shaped structures. This randomness makes the correlations for heat transfer and pressure loss based on sand grain roughness not applicable anymore. More in-depth research is needed to investigate the roughness effects. In this study, the AM roughness is modelled by a statistical distribution of spheres with different diameters using an upscale ratio of 77.4. An infrared (IR) camera was used to record the temperature distribution on the rough plates subjected to heated airflow. Three Re in the turbulent region (15000, 20000, 25000) were tested and the data from the IR camera were used to calculate the heat transfer coefficient (HTC) on the rough plate through a 3D finite element calibration solver. The results of averaged HTC agree well with data of the real Inconel 939 AM channel from which the upscaled rough plates are modelled. Also, the general patterns of HTC distributions matched the fluid dynamics analysis. Moreover, the results of arranging smooth and rough plates together shows that the heat transfer enhancement from SR is due to both the induced turbulent flows and the increased surface area. / Additiv tillverkning har i hög grad förbättrat designfriheten jämfört med traditionella tillverkningsprocesser som gjutning och fräsning. Att bygga lager för lager gör det möjligt att tillverka föremål med mycket mer komplexa former och strukturer. Denna egenskap är av särskilt intresse för tillverkning av turbinblad eftersom bättre interna kylkanaler kan uppnås för att förbättra den totala verkningsgraden hos en gasturbin. En egenskap hos additiv tillverkning är den relativt stora ytojämnheten, som påverkar både värmeöverföring och tryckförlust. Dess geometri är också unik med mycket slumpmässigt fördelade sfäriskt formade strukturerna. Denna slumpmässighet gör att de korrelationer för värmeöverföring och tryckförlust som baseras på sandkornens grovlek inte längre är tillämpliga. Mer djupgående forskning behövs för att undersöka grovhetseffekterna. I den här studien modelleras den additiva tillverkningens grovhet med en statistisk fördelning av sfärer med olika diametrar med ett uppskalningsförhållande på 77,4. En infraröd (IR) kamera användes för att registrera temperaturfördelningen på de skrovliga plattorna som utsattes för ett uppvärmt luftflöde. Tre Re i det turbulenta området (15000, 20000, 25000) testades och data från IR-kameran användes för att beräkna värmeöverföringskoefficientenpå den grova plattan genom en 3D finita elementkalibreringslösare. Resultaten av den genomsnittliga värmeöverföringskoefficienten stämmer väl överens med data från den verkliga additivt tillverkade Inconel 939-kanalen från vilken de uppskaladeg rova plattorna är modellerade. Även de allmänna mönstren för fördelningen av värmeöverföringskoefficienter stämmer överens med den fluiddynamiska analysen. Dessutom visar resultaten av att arrangera släta och grova plattor tillsammans att värmeöverföringsförbättringen från ytjämnhet beror på både de inducerade turbulenta flödena och den ökade ytarean.