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Academic literature on the topic 'Basler blaze 101'
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Dissertations / Theses on the topic "Basler blaze 101"
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Baruzzi, Francesco. "Object detection in robot picking applications using 3d cameras." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021. http://amslaurea.unibo.it/22594/.
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This work relies on analysis and testing of two 3D cameras in robot picking applications. Continuous progress in microelectronics, micro optics and micro technology made 3D cameras affordable and competitive with respect to 2D cameras in common industrial and commercial applications. 3D cameras, in fact, could give advantages in terms of timing and performances in application involving objects normally processed with 2D cameras. These cameras are intrinsically different in the technology used and provide mono/color images, depth maps and point clouds. First camera considered, Intel RealSense D435, is a stereo camera and the second one, Basler blaze 101, is a time of flight camera.
A particular focus is devoted to enhancing eventual advantages of using one technology with respect to the other. It’s important to underline that objects examined are quite small and heterogeneous in terms of material, opacity, colors, textures
and transparency.
Qualitative considerations will be done to a priori exclude from tests objects which depth maps result difficult to be created and exploited. Then, through computer vision algorithms, depth information are used to detect graspable objects and to get their positioning and orientations. These algorithms are capable of managing both isolated, touching or overlapping objects, establishing which one can be picked up and which not.
Three different algorithms will be deeply introduced and described with a detailed focus on best camera settings to accomplish these tasks.
Several analyses are done with both static and moving products on conveyor belts, varying conveyors colors and shapes.
Books on the topic "Basler blaze 101"
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Skovholt, Thomas M., and Len Jennings, eds. Master Therapists. Oxford University Press, 2016. http://dx.doi.org/10.1093/med:psych/9780190496586.001.0001.
Full textAbstract:
The search for the best outcomes in psychotherapy and counseling has been a long and winding trail. Traditional research methods attempting to quantify expertise have yet to map the complex path and characteristics of expert psychotherapists and counselors. This book blazes a new trail using extensive qualitative research methods to understand psychotherapy experts. Ten peer-nominated, active practitioners representing four different professions were interviewed by three interviewers for a total of over 100 hours. Based on the data from these interviews, we offer a portrait of the master therapist as well as an exploration of central characteristics, emotional wellness and resiliency of masters, how they construct the therapy relationship, ethical values of these experts, a history of the concept of expertise, and a description of our research methods. Master Therapists continues to be a valuable resource for counseling and therapy practitioners and scholars because it explicates the cognitive, emotional, and relational (CER) model of counseling expertise and provides the initial context for the more recent surge of expertise studies in counseling and psychotherapy. This research-based qualitative work provides essential signposts and markers on the road to psychotherapy expertise.
Conference papers on the topic "Basler blaze 101"
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Park, Jung Shin, Sang Hoon Lee, Jae Su Kwak, Won Suk Lee, and Jin Taek Chung. "Measurement of Blade Tip Heat Transfer and Leakage Flow in a Turbine Cascade With a Multi-Cavity Squealer Tip." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2072.
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Tip leakage flow induces high heat transfer to the blade tip and causes significant aerodynamic losses. In this paper, we propose a multi-cavity squealer tip with an additional rib in the squealer cavity. Our study investigated the effects of the rib location and shape on the blade tip heat transfer and the total pressure loss. Experiments were performed in a five-bladed linear cascade using a low speed wind tunnel. The blade chord, pitch, and span length were 126mm, 102.7mm, and 160mm, respectively. The Reynolds number, based on the blade chord and cascade exit velocity, was 2.44×105, and a tip clearance of 1.25% of the blade span was considered. The additional rib was installed in the squealer tip cavity near the leading edge, the mid-chord, and the training edge, respectively. The shape of the rib was also varied from rectangular to triangular in order to minimize the rib surface area exposed to the hot gas. The secondary flow and total pressure loss were measured using a seven-hole probe at one-chord downstream of the blade trailing edge, and the heat transfer coefficient distributions were measured by utilizing the hue-detection based transient liquid crystal technique. Flow measurement results indicated that the proposed multi-cavity tip reduced the total pressure loss. The blade tip heat transfer measurement results showed that the proposed multi-cavity tip was able to reduce the maximum heat transfer region near the cavity floor near the leading edge, but the heat transfer on the second cavity floor increased due to the leakage flow reattachment.
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De Maesschalck, C., S. Lavagnoli, and G. Paniagua. "Blade Tip Carving Effects on the Aero-Thermal Performance of a Transonic Turbine." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2028.
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Tip leakage flows in unshrouded high speed turbines cause large aerodynamic penalties, induce significant thermal loads and give rise to intense thermal stresses onto the blade tip and casing endwalls. In the pursuit of superior engine reliability and efficiency, the turbine blade tip design is of paramount importance and still poses an exceptional challenge to turbine designers. The ever-increasing rotational speeds and pressure loadings tend to accelerate the tip flow velocities beyond the transonic regime. Overtip supersonic flows are characterized by complex flow patterns, which determine the heat transfer signature. Hence, the physics of the overtip flow structures and the influence of the geometrical parameters on the overtip flow require further understanding to develop innovative tip designs. Conventional blade tip shapes are not adequate for such high speed flows and hence, potential for enhanced performances lays in appropriate tip shaping. The present research aims to quantify the prospective gain offered by a fully contoured blade tip shape against conventional geometries such as a flat and squealer tip. A detailed numerical study was conducted on a modern transonic turbine rotor blade (Reynolds number is 5.5 × 105, relative exit Mach number is 0.9) by means of three-dimensional Reynolds-Averaged Navier-Stokes calculations. The novel contoured tip geometry was designed based on a 2D tip shape optimization in which only the upper 2% of the blade span was modified. This study yields a deeper insight into the application of blade tip carving in high speed turbines and provides guidelines for future tip designs with enhanced aerothermal performances.
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Fabiano, Enrico, Dimitri J. Mavriplis, and Jayanarayanan Sitaraman. "Adjoint - based Aeroacoustic Design Optimization for Blade Vortex Interaction Noise." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1801.
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Kim, K. S., Youn J. Kim, and S. M. Kim. "Enhancement of Film Cooling Performance at the Leading Edge of Turbine Blade." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90321.
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To enhance the film cooling performance in the vicinity of the turbine blade leading edge, the flow characteristics of the film-cooled turbine blade have been investigated using a cylindrical body model. The inclination of the cooling holes is along the radius of the cylindrical wall and 20 deg relative to the spanwise direction. Mainstream Reynolds number based on the cylinder diameter was 1.01×105 and 0.69×105, and the mainstream turbulence intensities were about 0.2% in both Reynolds numbers. CO2 was used as coolant to simulate the effect of density ratio of coolant-to-mainstream. Furthermore, the effect of coolant flow rates was studied for various blowing ratios of 0.4, 0.7, 1.1, and 1.4, respectively. In experiment, spatially-resolved temperature distributions along the cylindrical body surface were visualized using infrared thermography (IRT) in conjunction with thermocouples, digital image processing, and in situ calibration procedures. This comparison shows the results generated to be reasonable and physically meaningful. The film cooling effectiveness of current measurement (0.29 mm × 0.33 min per pixel) presents high spatial and temperature resolutions compared to other studies. Results show that the blowing ratio has a strong effect on film cooling effectiveness and the coolant trajectory is sensitive to the blowing ratio. The local spanwise-averaged effectiveness can be improved by locating the first-row holes near the second-row holes.
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Glezer, B., H. K. Moon, and T. O’Connell. "A Novel Technique for the Internal Blade Cooling." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-181.
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Development of an adequate air cooling system for the thermally highly loaded leading edge and tip of the blade, that is cost effective and also relatively insensitive to manufacturing tolerances and operating environment continues to be one of the major challenges in advanced gas turbine design. Extensive studies on the convective (including impingement) and film cooling techniques produced remarkable progress in achieving a high cooling effectiveness level for turbine airfoils. However, in the case of turbine blades, application of these techniques has severe limitations. Highly effective impingement cooling needs to be combined with film discharge of the spent air to avoid a negative impact of crossflow on internal heat transfer and also provide additional thermal protection of the surface downstream of the discharge holes. Noticeable aerodynamic penalties, stress concentration and significant increase in manufacturing cost limit application of blade film cooling, particularly for moderately high operating temperatures. Search for a highly effective robust design of internal airfoil cooling which can delay the use of film cooling resulted in the creation of a new technique which is described in this paper. This technique is based on generation of a swirling flow structure in the blade internal leading edge passage. Significant heat transfer augmentation can be achieved when the cooling air is delivered into the leading edge plenum tangentially to the inner concave surface. The best results can be obtained when the swirling flow is allowed to move radially, creating a three-dimensional screw-shaped flow in the plenum. The presented results of the flow and heat transfer studies performed for the practical range of Reynolds numbers for the internal flow show that the leading edge screw-shaped cooling technique provides internal heat transfer rate comparable with impingement coupled with film discharge of the spent air, is more effective than impingement with cross flow and is almost five times higher than heat transfer in the smooth channel.
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Clough, H. J. "Blade Excitation Criteria Developed for Aero Derived Engines in Arctic Alaska." In ASME 1987 International Gas Turbine Conference and Exhibition. American Society of Mechanical Engineers, 1987. http://dx.doi.org/10.1115/87-gt-104.
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Aero derived gas turbines are now used for land based power generation throughout the world. Virtually all of these engine types stem from proven designs that have achieved many thousands of hours of reliable operation in the demanding aircraft environment.
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Bhargava, R., R. Raj, and D. R. Boldman. "Wall Shear Stress Measurement in Blade End-Wall Corner Region." In ASME 1987 International Gas Turbine Conference and Exhibition. American Society of Mechanical Engineers, 1987. http://dx.doi.org/10.1115/87-gt-181.
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Experimental results on the local wall shear stress vector and surface pressure measurements upstream and in the blade end-wall corner region are presented in this paper. The measurements were obtained at a free stream velocity of 27.3 m/s with the Reynolds number based on Preston tube outer diameter and friction velocity varying from 30 to 100. A specially constructed Preston tube, the tip of which can be concentrically rotated about its axis of rotation at the measurement location, was employed for the measurement of wall shear stress vector. The magnitude of the wall shear stress in the vicinity of the corner was observed to increase significantly (≈170 % max.) compared to its far upstream value. This increase was consistently found to be higher on the blade surface compared to its value on the plate surface of the blade end-wall corner. On both the surfaces in the blade end-wall corner, the variation of the wall shear stress direction was found to be more predominant in the vicinity of the blade leading edge location. The trend of the measured wall shear stress direction showed good agreement with the limiting streamline directions obtained from the flow visualization studies. The surface pressure variation, at any axial station in the corner region, on the flat plate part of the blade end-wall corner was found to be relatively larger than on the blade surface. Some plausible explanation for the observed variation in the local wall shear stress and surface pressure in the blade end-wall corner are described here.
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Ranft, Kirsten, Ali A. Ameri, J. Iwan D. Alexander, and Edmane Envia. "Acoustic Analysis of the NREL Phase VI Wind Turbine." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23785.
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The aim of this work is to predict the aerodynamic noise emitted from the NREL Phase VI Wind Turbine [1]. Specifically rotational noise and broadband noise of the blade have been investigated. The approach to predict aeroacoustic noise is based on the acoustic analogy [2]. In acoustic analogy, the sources of aerodynamic noise are derived from the flow equations and the resulting radiated noise is calculated using the Ffowcs Williams and Hawkings equation [3]. Thus, the prediction of aerodynamic noise requires an accurate solution of the flow field. In this work the flow field around the blade has been modeled using FLUENT’s k-ω SST turbulence model. A hybrid grid containing approximately 1.5 × 106 tetrahedral and prismatic elements has been created. The near field around the blade is a structured O-grid with 100 cells along the chord and 50 cells normal to the blade surface. To obtain the resolution of the viscous sublayer, a y+ of approximately unity has been chosen. For the flow computation a simple scheme is used with a second order upwind method and wind speeds of 7m/s, 10m/s and 25 m/s, respectively and a rotor rotation speed of 72 rpm.
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Arisi, A., S. Xue, W. F. Ng, H. K. Moon, and L. Zhang. "Numerical Investigation of Aerothermal Characteristics of the Blade Tip and Near-Tip Regions of a Transonic Turbine Blade." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25492.
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In modern gas turbine engines, the blade tips and near-tip regions are exposed to high thermal loads caused by the tip leakage flow. The rotor blades are therefore carefully designed to achieve optimum work extraction at engine design conditions without failure. However, very often gas turbine engines operate outside these design conditions which might result in sudden rotor blade failure. Therefore, it is critical that the effect of such off-design turbine blade operation be understood to minimize the risk of failure and optimize rotor blade tip performance. In this study, the effect of varying the exit Mach number on the tip and near-tip heat transfer characteristics was numerically studied by solving the steady Reynolds Averaged Navier Stokes (RANS) equation. The study was carried out on a highly loaded flat tip rotor blade with 1% tip gap and at exit Mach numbers of Mexit = 0.85 (Reexit = 9.75 × 105) and Mexit = 1.0 (Reexit = 1.15 × 106) with high freestream turbulence (Tu = 12%). The exit Reynolds number was based on the rotor axial chord. The numerical results provided detailed insight into the flow structure and heat transfer distribution on the tip and near-tip surfaces. On the tip surface, the heat transfer was found to generally increase with exit Mach number due to high turbulence generation in the tip gap and flow reattachment. While increase in exit Mach number generally raises he heat transfer over the whole blade surface, the increase is significantly higher on the near-tip surfaces affected by leakage vortex. Increase in exit Mach number was found to also induce strong flow relaminarisation on the pressure side near-tip. On the other hand, the size of the suction surface near-tip region affected by leakage vortex was insensitive to changes in exit Mach number but significant increase in local heat transfer was noted in this region.
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Narzary, Diganta P., Kuo-Chun Liu, and Je-Chin Han. "Influence of Coolant Density on Turbine Blade Platform Film-Cooling." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59342.
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Detailed parametric study of film-cooling effectiveness was carried out on a turbine blade platform of a five-blade linear cascade. The parameters chosen were — freestream turbulence intensity, upstream stator-rotor purge flow rate, discrete-hole film-cooling blowing ratio, and coolant-to-mainstream density ratio. The measurement technique adopted was temperature sensitive paint (TSP) technique. Two turbulence intensities of 4.2% and 10.5%; three purge flows between the range of 0.25% and 0.75% of mainstream flow rate; three blowing ratios between 1.0 and 2.0; and three density ratios between 1.1 and 2.1 were investigated. Purge flow was supplied via a typical double-toothed stator-rotor seal, whereas the discrete-hole film cooling was accomplished via two rows of cylindrical holes arranged along the length of the platform. The inlet and the exit Mach numbers were 0.27 and 0.44, respectively. Reynolds number of the mainstream flow was 7.5*105 based on the exit velocity and chord length of the blade. Results indicated that platform film-cooling effectiveness decreased with turbulence intensity, increased with purge flow rate and density ratio, and possessed an optimum blowing ratio value. The improved effectiveness with density ratio was further validated by the pressure sensitive paint (PSP) technique.