Relevant bibliographies by topics / Hot Holes Injection Erasing

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Academic literature on the topic 'Hot Holes Injection Erasing'

Author: Grafiati
Published: 25 May 2024

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Journal articles on the topic "Hot Holes Injection Erasing"

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Chen, Shen Li, and Shun Tai Chung. "Charge Programming and Erasing Characteristics of the Submicron Stacked-Gate Flash Cells." Advanced Materials Research 634-638 (January 2013): 2446–49. http://dx.doi.org/10.4028/www.scientific.net/amr.634-638.2446.

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A non-Maxwellian hot-carrier generation current model for simulation of charge injection and erasing in the 0.35um flash EEPROM device is presented in this paper. Unlike the conventional model, which is based on the local electric fields in the device, and it accounts for non-local effects resulting from the large variations in electric field in a submicron flash EEPROM. Good agreements between the measured and calculated results in the charge writing and the Fower-Nordheim erasing operations.
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Jin, Yuxuan, and Zefeng Chen. "High gain hot-carrier WSe2 phototransistor with gate-tunable responsivity." Advances in Engineering Technology Research 7, no. 1 (July 26, 2023): 21. http://dx.doi.org/10.56028/aetr.7.1.21.2023.

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Hot-carrier injection at semiconductor/metal interface shows great potentials in infrared photodetection. However, the photoresponsivity of hot-carrier photodetector with diode mode is still limited in the scale of 1 mA/W due to the low injection efficiency of hot carriers and the lack of gain. Here, we demonstrate a high gain hot-carrier WSe2 phototransistor with gate-tunable responsivity. In this device, plasmonic resonances is used to enhance the light absorption of gold nanodisk, which provide hot holes. The hot holes are trapped into WSe2 and recycled in WSe2 channel in lateral direction, which introduce high gain for photodetection. Experiment shows that the photoresponsivity of the device can be over 0.23 A/W with a gain of 270 at the wavelength of 1310 nm. More interestingly, the responsivity of the device can be tuned by gate, which can be used to encode synaptic weights of the sensor pixel.
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Sun, Lei, Liyang Pan, Huiqing Pang, Ying Zeng, Zhaojian Zhang, John Chen, and Jun Zhu. "Characteristics of Band-to-Band Tunneling Hot Hole Injection for Erasing Operation in Charge-Trapping Memory." Japanese Journal of Applied Physics 45, no. 4B (April 25, 2006): 3179–84. http://dx.doi.org/10.1143/jjap.45.3179.

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4

Manzini, S., and A. Gallerano. "Avalanche injection of hot holes in the gate oxide of LDMOS transistors." Solid-State Electronics 44, no. 7 (July 2000): 1325–30. http://dx.doi.org/10.1016/s0038-1101(99)00317-2.

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Jeong, Yoon Seong, and Jun Su Park. "Effect of Inlet Compound Angle of Backward Injection Film Cooling Hole." Energies 13, no. 4 (February 13, 2020): 808. http://dx.doi.org/10.3390/en13040808.

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Backward injection film cooling holes were studied to improve film cooling effectiveness using simple cylindrical holes, and this principle was applied to an actual gas turbine. Although film cooling effectiveness was improved using a backward injection film cooling hole, the backward flow of combustion gas from the backward injection cooling hole was one of the major reasons for cracks in the hot components. To prevent cracks and backward flow in the backward injection film cooling hole, this study changed the inlet compound angle of the backward injection film cooling hole. Numerical analysis using CFX v. 17.0 was performed to calculate the flow characteristics and film cooling effectiveness of backward injection film cooling. Aa a result, the effect of the inlet compound angle of the backward injection film cooling hole was confirmed to prevent the backward flow, which increased upon increasing the inlet compound angle. This study shows that the backward flow and cracks in the backward injection film cooling hole can be prevented simply by changing the inlet compound angle.
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Williamson, J. G., H. van Houten, C. W. J. Beenakker, M. E. I. Broekaart, L. I. A. Spendeler, B. J. van Wees, and C. T. Foxon. "Injection of ballistic hot electrons and cool holes in a two-dimensional electron gas." Surface Science 229, no. 1-3 (April 1990): 303–6. http://dx.doi.org/10.1016/0039-6028(90)90894-e.

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7

Liu, Jian, Mengyao Xu, and Wenxiong Xi. "Effects of Gas Thermophysical Properties on the Full-Range Endwall Film Cooling of a Turbine Vane." Aerospace 10, no. 7 (June 28, 2023): 592. http://dx.doi.org/10.3390/aerospace10070592.

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To protect turbine endwall from heat damage of hot exhaust gas, film cooling is the most significant method. The complex vortex structures on the endwall, such as the development of horseshoe vortices and transverse flow, affects cooling coverage on the endwall. In this study, the effects of gas thermophysical properties on full-range endwall film cooling of a turbine vane are investigated. Three kinds of gas thermophysical properties models are considered, i.e., the constant property gas model, ideal gas model, and real gas model, with six full-range endwall film cooling holes patterns based on different distribution principles. From the results, when gas thermophysical properties are considered, the coolant coverage in the pressure side (PS)-vane junction region is improved in Pattern B, Pattern D, Pattern E, and Pattern F, which are respectively designed based on the passage middle gap, limiting streamlines, heat transfer coefficients (HTCs), and four-holes pattern. Endwall η distribution is mainly determined by relative ratio of ejecting velocity and density of the hot gas and the coolant. For the cooling holes on the endwall with an injection angle of 30°, the density ratio is more dominant in determining the coolant coverage. At the injection angle of 45°, i.e., the slot region, the ejecting velocity is more dominant in determining the coolant coverage. When the ejecting velocity Is large enough from the slot, the coolant coverage on the downstream endwall region is also improved.
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Lin, Y. L., and T. I. P. Shih. "Film Cooling of a Cylindrical Leading Edge With Injection Through Rows of Compound-Angle Holes." Journal of Heat Transfer 123, no. 4 (January 9, 2001): 645–54. http://dx.doi.org/10.1115/1.1370513.

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Computations, based on the k-ω shear-stress transport (SST) turbulence model in which all conservation equations were integrated to the wall, were performed to investigate the three-dimensional flow and heat transfer about a semi-cylindrical leading edge with a flat afterbody that is cooled by film-cooling jets, injected from a plenum through three staggered rows of compound-angle holes with one row along the stagnation line and two rows along ±25 deg. Results are presented for the surface adiabatic effectiveness, normalized temperature distribution, velocity vector field, and surface pressure. These results show the interactions between the mainstream hot gas and the cooling jets, and how those interactions affect surface adiabatic effectiveness. Results also show how “hot spots” can form about the stagnation zone because of the flow induced by the cooling jets. The computed results were compared with experimental data generated under a blind test. This comparison shows the results generated to be reasonable and physically meaningful. With the SST model, the normal spreading was under predicted from 20 to 50 percent. The lateral spreading was over predicted above the surface, but under predicted on the surface. The laterally averaged surface effectiveness was well predicted.
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Gustafsson, K. M. Bernhard, and T. Gunnar Johansson. "An Experimental Study of Surface Temperature Distribution on Effusion-Cooled Plates." Journal of Engineering for Gas Turbines and Power 123, no. 2 (January 23, 2001): 308–16. http://dx.doi.org/10.1115/1.1364496.

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A parametric study of temperature distribution on effusion-cooled plates under conditions typical for combustion chambers was performed using infrared thermography. In this investigation, the effects of different temperature ratios, velocity ratios of the two air streams, the injection hole spacing, inclination angle of the injection holes, and the thermal heat conductivity of the plates were studied. For a given amount of cooling air, the cooling efficiency was found to increase markedly with a reduction in hole spacing, i.e., when the number of holes was increased. Reducing the injection angle results in more attached jets, especially for small amounts of cooling air, and marginally lowers the wall temperature. A high thermal conductivity of the plate was found to decrease its surface temperature in front of the first row of holes but not the mean temperature in downstream positions. The most important operational parameters were the temperature ratio and the velocity ratio of the hot and cold air streams. An almost linear relation was found between the temperature ratio and the surface temperature when the jet velocity was large compared to the crossflow velocity. For plates with sparse hole spacing, a change in the velocity ratio had a small effect on the surface temperature, whereas the effect was large for dense hole spacings and the same amount of cooling air.
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Kafaei, Amir, Fahime Salmani, Esmail Lakzian, Włodzimierz Wróblewski, Mikhail S. Vlaskin, and Qinghua Deng. "The best angle of hot steam injection holes in the 3D steam turbine blade cascade." International Journal of Thermal Sciences 173 (March 2022): 107387. http://dx.doi.org/10.1016/j.ijthermalsci.2021.107387.

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Conference papers on the topic "Hot Holes Injection Erasing"

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Sun, Lei, Liyang Pan, Huiqing Pang, Ying Zeng, Zhaojian Zhang, John Chen, and Jun Zhu. "Characteristics of Band-to-Band Hot Hole Injection for Erasing Operation in Charge Trapping Memory." In 2005 International Conference on Solid State Devices and Materials. The Japan Society of Applied Physics, 2005. http://dx.doi.org/10.7567/ssdm.2005.p4-4.

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Mohd Khosru, QUAZI Deen, Naoki YASUDA, Akinori MARUYAMA, Kenji TANIGUCHI, and Chihiro HAMAGUCHI. "Spatial Distribution of Trapped Holes in the Oxide of MOSFETs after Uniform Hot-Hole Injection." In 1991 International Conference on Solid State Devices and Materials. The Japan Society of Applied Physics, 1991. http://dx.doi.org/10.7567/ssdm.1991.a-1-3.

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Park, Sehjin, Eui Yeop Jung, Seon Ho Kim, Ho-Seong Sohn, and Hyung Hee Cho. "Enhancement of Film Cooling Effectiveness Using Backward Injection Holes." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43853.

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Film cooling is a cooling method used to protect the hot components of a gas turbine from high temperature conditions. For this purpose, high and uniform film cooling effectiveness is required to protect the vanes/blades from excessive thermal stress. Backward injection is proposed as one of the methods for the improvement of film cooling effectiveness. In this study, experiments were performed to investigate the effect of backward injection on film cooling effectiveness, using pressure sensitive paint (PSP) method. Four experimental configurations were composed of forward and backward injection cylindrical holes. The cylindrical holes were aligned in two staggered rows with pitch (p) of 6d and row spacing (s) of 3d. The injection angles (α) of the cylindrical holes were 35° and 145° for forward and backward injection, respectively. The blowing ratios (M) ranged from 0.5 to 2.0 and the density ratio (DR) was about 1. The results indicate that backward injection enhanced not only film cooling effectiveness but also the lateral cooling uniformity. At a high blowing ratio, all configurations demonstrated higher film cooling effectiveness with backward injection than with only forward injection; thus, the dispersion of the backward injection jets enhanced the lateral coverage over wide areas. Configuration, in particular, arranged with forward injection in the first row and backward injection in the second row, obtained the highest film cooling effectiveness among the four cases studied, due to the dispersion of the backward injection jets and the coolant supply from the forward injection jets at a high blowing ratio.
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Subbuswamy, Ganesh, Xianchang Li, and Kunal Gharat. "Numerical Simulation of Backward Film Cooling With Fan-Shaped Holes." In ASME 2013 Heat Transfer Summer Conference collocated with the ASME 2013 7th International Conference on Energy Sustainability and the ASME 2013 11th International Conference on Fuel Cell Science, Engineering and Technology. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/ht2013-17801.

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The thermal efficiency of a gas turbine is largely dependent on the turbine inlet temperature (TIT). Modern gas turbines may operate at temperatures as high as 2000K, which is higher than the melting point of the material in use. Hence, thermal protection of gas turbine hot components is a big challenge. Film cooling is the most common cooling technique adopted in this application. In film cooling, coolant is injected at discrete locations along the metal surface, which forms a layer of cool air immediately over the hot surface, thus, protecting it from direct contact with hot mainstream air. The cooling is strong along the centerline of the hole in the downstream region and rapidly decreases over the span-wise direction. The distributed cooling can result in large thermal gradients, inducing thermal stresses in the material. The region with least cooling may lead to a cascade failure of the blade. Film cooling with backward injection holes has been proved to reduce this effect. In the current work, backward coolant injection scheme is explored under fan-shaped holes numerically. Fluent, a commercial CFD software, is used in the current work for numerical simulations. Effects of blowing ratio, injection angle, and turbulence are considered. Numerical results show that fan-shaped holes are better than simple cylindrical holes in terms of both cooling effectiveness and its uniformity. Numerical results are validated with experimental results. The image of temperature fields on cooling surface is captured with an Infrared camera.
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Lin, Y. L., M. A. Stephens, and T. I.-P. Shih. "Computation of Leading-Edge Film Cooling With Injection Through Rows of Compound-Angle Holes." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-298.

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Computations were performed to investigate the three-dimensional flow and heat transfer about a semi-cylindrical leading edge with a flat afterbody that is cooled by film-cooling jets, injected through three staggered rows of compound-angle holes with one row along the stagnation line and two rows along ±25°. Results are presented for the surface adiabatic effectiveness, temperature distribution, velocity vector field, turbulent kinetic energy, and surface pressure. These results show the interactions between the mainstream hot gas and the cooling jets, and how those interactions affect surface adiabatic effectiveness. The computed results were compared with experimental data generated under a blind test, and reasonably good agreements were obtained. This computational study is based on the ensemble-averaged conservation equations of mass, momentum (compressible Navier-Stokes), and energy closed by a low Reynolds number k-ω turbulence model. Solutions were generated by a cell-centered finite-volume method that uses second-order accurate flux-difference splitting of Roe on a multiblock structured grid system. In the computations, the flow is resolved not just in the region about the leading edge, but also inside the film-cooling holes and in the plenum where the cooling flow emerges.
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Shine, S. R., S. Sunil Kumar, and B. N. Suresh. "Internal Wall-Jet Film Cooling With Tangential Coolant Holes." In ASME 2012 Gas Turbine India Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gtindia2012-9607.

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Experimental and numerical investigations are carried out to analyze the effect of tangential coolant injection on overall film cooling performance in a cylindrical test section simulating a high curvature surface. Experiments are conducted using hot air as core gas and nitrogen gas as coolant injected through cylindrical holes inclined at 30-degrees to the core gas flow. A three-dimensional multi-species numerical model is formulated using the finite volume formulation and is validated using the obtained experimental data. Simulation results indicate that an optimum blowing ratio exists for which the effectiveness is maximum. The conjugate effectiveness is observed to be higher than adiabatic effectiveness values except in the vicinity of injection owing to the wall conduction effects. Numerical analysis performed with an annular slot placed at the exit of the coolant holes showed an increase in the effectiveness by 21 % compared to the base hole. It is expected that the knowledge acquired in this study has the potential to support new ideas in gas turbine film cooling techniques such as turbine casing film cooling.
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Natsui, G., P. L. Johnson, M. C. Torrance, M. A. Ricklick, and J. S. Kapat. "The Effect of Transpiration on Discrete Injection for Film Cooling." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-46138.

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A segment of permeable wall is installed near a row of cylindrical film holes, parallel to the flow and inclined at 35 degrees. Coolant is forced through both the permeable wall and the film holes resulting in a downstream film composed of both transpired and discretely injected coolant. The permeable wall extends 1.5 cylindrical hole diameters in the flow direction. The effects on the aerodynamic performance and cooling downstream of the row of cylindrical holes in the presence of transpiration is studied numerically with a procedure validated by hot-wire anemometer and temperature sensitive paint measurements. The hydrodynamic boundary layer in the presence of film and adiabatic film cooling effectiveness downstream of single and coupled film sources are compared with numerical predictions. The performance of the coolant film is predicted in order to understand the sensitivity of cooling and aerodynamic losses on the relative positioning of the two sources at each blowing ratio. The results indicate that a coupling of the two sources allows a more efficient use of coolant by generating a more uniform initial film. With careful optimization the discrete holes can be placed farther apart laterally and operate at a lower blowing ratio with a transpiration segment making the large deficits in cooling effectiveness mid-pitch less severe, overall minimizing coolant usage. Comparisons of linear superposition predictions of the two independent sources with the corresponding coupled scenario indicate the two films positively influence one another and surpass additive predictions of cooling. All relative placements have an overall beneficial effect on the cooling seen by the protected wall. Some cases show an increase in area-averaged film cooling effectiveness of 300% along with a 50% increase in aerodynamic loss coefficient by injecting an additional 10% coolant. In this study the downstream transpiration placement is found to perform best of the three geometries tested while considering cooling, aerodynamic losses, local uniformity and manufacturing feasibility. With further study and optimization this technique can potentially provide more effective thermal protection at a lower cost of aerodynamic losses and spent coolant.
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Heneka, Christian, Achmed Schulz, Hans-Jo¨rg Bauer, Andreas Heselhaus, and Michael E. Crawford. "Film Cooling Performance of Sharp-Edged Diffuser Holes With Lateral Inclination." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23090.

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An experimental study on film cooling performance of laterally inclined diffuser shaped cooling holes is presented. The measurements have been conducted on a flat plate with coolant ejected from a plenum. The film cooling effectiveness downstream of a row of four laidback fanshaped holes with sharp-edged diffusers has been determined by means of IR thermography. A variety of geometric parameters has been tested, including the inclination angle, the compound angle, the area ratio, and the pitch to diameter ratio. All tests have been performed over a wide range of engine typical blowing ratios (M = 0.5–3.0). The hot gas Reynolds number and the coolant to hot gas density ratio have been kept constant close to engine realistic conditions. The results, presented in terms of contour plots of related adiabatic film cooling effectiveness as well as laterally averaged related values, clearly show the influences of the cooling hole geometry. Increasing the area ratio and the compound angle, in general, leads to higher values of the effectiveness, whereas steeper injection causes a reduction of the effectiveness.
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Li, Xianchang, and Ting Wang. "Simulation of Film Cooling Enhancement With Mist Injection." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-69100.

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Cooling of gas turbine hot section components such as combustor liners, combustor transition pieces, turbine vanes (nozzles) and blades (buckets) is a critical task for improving the life and reliability of hot-section components. Conventional cooling techniques using air-film cooling, impingement jet cooling, and turbulators have significantly contributed to cooling enhancements in the past. However, the increased net benefits that can be continuously harnessed by using these conventional cooling techniques seem to be incremental and are about to approach their limit. Therefore, new cooling techniques are essential for surpassing these current limits. This paper investigates the potential of film cooling enhancement by injecting mist into the coolant. The computational results show that a small amount of injection (2% of the coolant flow rate) can enhance the cooling effectiveness about 30% ∼ 50%. The cooling enhancement takes place more strongly in the downstream region, where the single-phase film cooling becomes less powerful. Three different holes are used in this study including a 2-D slot, a round hole, and a fan-shaped diffusion hole. A comprehensive study is performed on the effect of flue gas temperature, blowing angle, blowing ratio, mist injection rate, and droplet size on the cooling effectiveness with 2-D cases. Analysis on droplet history (trajectory and size) is undertaken to interpret the mechanism of droplet dynamics.
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McGovern, Kevin T., and James H. Leylek. "A Detailed Analysis of Film Cooling Physics: Part II — Compound–Angle Injection With Cylindrical Holes." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-270.

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Detailed analyses of computational simulations with comparisons to experimental data were performed to identify and explain the dominant flow mechanisms responsible for film cooling performance with compound angle injection, Φ, of 45°, 60°, and 90°. A novel vorticity and momentum based approach was implemented to document how the symmetric, counter–rotating vortex structure typically found in the crossflow region in streamwise injection cases, becomes asymmetric with increasing Φ. This asymmetry eventually leads to a large, single vortex system at Φ = 90° and fundamentally alters the interaction of the coolant jet and hot crossflow. The vortex structure dominates the film cooling performance in compound angle injection cases by enhancing the mixing of the coolant and crossflow in the near wall region, and also by enhancing the lateral spreading of the coolant. The simulations consist of fully–elliptic and fully–coupled solutions for field results in the supply plenum, film–hole, and crossflow regions and includes surface results for adiabatic effectiveness η and heat transfer coefficient h. Realistic geometries with length–to–diameter ratio of 4.0 and pitch–to–diameter ratio of 3.0 allowed for accurate capturing of the strong three–way coupling of flow in this multi–region flowfield. The cooling configurations implemented in this study exactly matched experimental work used for validation purposes and were represented by high quality computational grid meshes using a multi–block, unstructured grid topology. Blowing ratios of 1.25 and 1.88, and density ratio of 1.6 were used to simulate realistic operating conditions and to match the experiments used for validation. Predicted results for η and h show good agreement with experimental data.
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