Academic literature on the topic 'Blade to blade chanel (Intel-blade chanel)'
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Journal articles on the topic "Blade to blade chanel (Intel-blade chanel)"
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Gribin, Vladimir, Ilya Gavrilov, Aleksandr Tishchenko, Victor Tishchenko, Vitaliy Popov, Sergey Khomyakov, and Roman Alexeev. "Features of liquid phase movement in the inter-blade channel of nozzle blade cascade." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 5 (September 13, 2017): 452–60. http://dx.doi.org/10.1177/0957650917730947.
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The experimental results of wet steam flow in the blade channel of flat nozzle blade cascade have been considered in the paper. The aim of this work is to study the motion of liquid droplets inside the inter-blade channel. Experimental studies were performed on installation circuit of wet steam. In order to obtain velocity fields of droplets in investigated channel, the laser diagnostics system was used. It carries out the cross-correlation method—particle tracking velocimetry. Numerical simulation of wet steam flow in studied channel was performed. According to the obtained data, the main features of the droplets motion in the blade channel have been revealed. Basic droplets streams and the sources of their appearance have been determined. The process of deposition and breakdown of the droplets on the surface of the blades have been studied. It is shown that reflected region of droplets (“fountain”) is formed around the leading edge. The experimental data were compared with the results of numerical simulation of the droplets motion in the flat nozzle blade cascade.
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Zhang, Jinfeng, Guidong Li, Jieyun Mao, Shouqi Yuan, Yefei Qu, and Jing Jia. "Effects of the outlet position of splitter blade on the flow characteristics in low-specific-speed centrifugal pump." Advances in Mechanical Engineering 10, no. 7 (July 2018): 168781401878952. http://dx.doi.org/10.1177/1687814018789525.
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To elucidate the influences of the outlet position of splitter blades on the performance of a low-specific-speed centrifugal pump, two different splitter blade schemes were proposed: one located in the middle of the channel and the other having a deviation angle at the trailing edge of splitter blade toward the suction side of the main blade. Experiments on the model pump with different splitter blade schemes were conducted, and numerical simulations on internal flow characteristics in the impellers were studied by means of the shear stress transport k- ω turbulence model. The results suggest that there is a good agreement between the experimental and numerical results. The splitter blade schemes can effectively optimize the structure of the jet-wake pattern and improve the internal flow states in the impeller channel. In addition, the secondary flow and inlet circulation on the pressure surface of main blade, the flow separation on the suction side of splitter blade, the pressure coefficient distributions on blade surface can achieve an evident amelioration when the trailing edge of splitter blade toward the suction side of the main blade is mounted at an appropriate position.
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Zhao, Wenbin, Jianbin Hu, and Kai Wang. "Influence of Channel-Diffuser Blades on Energy Performance of a Three-Stage Centrifugal Pump." Symmetry 13, no. 2 (February 5, 2021): 277. http://dx.doi.org/10.3390/sym13020277.
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In order to improve hydraulic efficiency, influence of inlet angle, outlet angle, wrap angle, inlet shape and outer edge camber lines of channel-diffuser blades on the energy performance of a three-stage centrifugal pump were studied and the pressure distributions on the blade of the first-stage channel-diffuser were particularly analyzed. The result shows that the efficiency of the pump is maximal when the blade inlet angle is 12°. The pressure variation in the model with the inlet angle of 12° was small and the amplitude of fluctuation was also not large. When the outlet angle was 90°, the pressure distribution in the outlet of the blades that are symmetrically distributed along the center of the diffuser shell was significantly better than that with other outlet angles. The effect of the blade wrap angle of the channel-diffuser on the energy performance of the pump was relatively small. The internal flow in the diffuser with the diffusion inlet shapes was steady for both the convex surface and concave surface. The diffusion inlet of the channel-diffuser blade corresponded to the outlet region of the impeller blade, which reflected a good matching. The fluctuation amplitude and the distribution range of the models with a uniform transition were smaller than those with non-uniform transition. In order to verify the effectiveness of the research results, an experimental test was carried out on the pump. The results show that when the flow rate is 850 m3/h, the head of the pump is 138.67 m and the efficiency of pump is 69.48%.
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Суббота, Анатолий Максимович, and Виталий Георгиевич Джулгаков. "ПОВЫШЕНИЕ ЭФФЕКТИВНОСТИ ВЕТРОЭНЕРГЕТИЧЕСКОЙ УСТАНОВКИ С ВЕРТИКАЛЬНОЙ ОСЬЮ ВРАЩЕНИЯ." RADIOELECTRONIC AND COMPUTER SYSTEMS, no. 1 (February 23, 2018): 77–86. http://dx.doi.org/10.32620/reks.218.1.10.
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The questions connected with increase of efficiency of functioning of a wind power plant with a vertical axis of rotation are considered.Such plants convert the energy of the wind flow into rotational energy of the generator shaft, pump or other actuators. An overview of the design options for wind turbines of this type is presented. For vertically-axial wind power plants, in comparison with horizontally-propeller ones, it is possible to increase their efficiency by providing insensitivity to wind direction change. This is possible provided that the angular position of the blades with respect to the wind flow is continuously and purposefully changed as the wind turbine rotates. The principle of increasing the efficiency of the wind power plant is proposed due to the synchronous control of the position of the blades, depending on the direction and speed of the wind flow. The implementation of this principle is considered in detail for a four-bladed wind turbine. Depending on the direction and magnitude of the wind flow, as well as the angular velocity of rotation of the turbine, the value of the angle of the initial installation of the blades was analytically obtained, which ensures the maximum efficiency of using the wind plant. The functional scheme of the control system of the orientation of the four blades is formed. This system uses information about the current power of the generator, the rotation speed of the wind turbine, the direction and speed of the wind flow, obtained from the respective sensors. A detailed functional diagram of one channel of the control system has been constructed taking into account the initial exposure of the blade, which additionally uses information about the current angular position of the blade and the speed of its turn. Each such channel contains a proportional-differential controller or fuzzy logic controller. The proposed fuzzy controller has two inputs of linguistic variables - the angle of rotation of the blade and the speed of its rotation. As a kind of membership functions, a triangular distribution is chosen. A system of rules for adjusting the fuzzy controller has been developed. The computer simulation of the channel functioning of the control system with two types of regulators for the mode of initial setting of the blades with a change in wind direction was performed. Comparison of the quality of the control system with a proportional-differential and fuzzy controller is performed
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Wang, Peng, Xinyu Zhu, and Yi Li. "Analysis of Flow and Wear Characteristics of Solid–Liquid Two-Phase Flow in Rotating Flow Channel." Processes 8, no. 11 (November 21, 2020): 1512. http://dx.doi.org/10.3390/pr8111512.
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To study the flow characteristics and the wear distribution of pumps at different rotation speeds, a rotating disc with three blades was designed for experiments. Numerical simulations were conducted using a computational fluid dynamics-discrete phase model (CFD–DPM) approach. The experimental and numerical results were compared, and the flow characteristics and wear behaviors were determined. As the speed increased, the particles at the blade working surface aggregated. The particle velocity gradually increased at the outlet of the channel. The severe wear areas were all located in the outlet area of the blade working surface, and the wear area extended toward the inlet area of the blade with increasing speed. The wear rate of the blade surface increased as the speed increased, and an area with a steady wear rate appeared at the outlet area of the blade. When the concentration was more than 8%, the severe wear areas were unchanged at the same speed. When the speed increased, the severe wear areas of the blade produced wear ripples, and the area of the ripples increased with increasing speed. The height difference between the ripples along the flow direction on the blade became larger as the speed increased.
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Fan, Hong-Zhou, Shang-Jin Wang, Guang Xi, and Yan-Long Cao. "A novel tool-path generation method for five-axis flank machining of centrifugal impeller with arbitrary surface blades." Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture 231, no. 1 (August 8, 2016): 155–66. http://dx.doi.org/10.1177/0954405415599943.
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The centrifugal impeller with arbitrary surface blades is a very important component in automobile, ships, and aircraft industry, and it is one of the most difficult parts to process. Focusing on the machining efficiency improvement, combining the geometric advantages of ruled surface and arbitrary surface, and utilizing the efficient and accurate advantages of flank machining and point machining, this article presents a novel and targeted tool-path generation method and algorithm for five-axis flank machining of centrifugal impeller with arbitrary surface blades. In light of specific characters of different surfaces, the analyses of two different impeller blades are proposed first, the more characteristic and complex geometrical structures of the arbitrary blade are achieved. In rough machining, an approximate ruled surface blade is obtained, and a simple channel is achieved; the flank milling of the centrifugal impeller with ruled surface blades is achieved relative to the point milling of the centrifugal impeller with arbitrary surface blades; and the triangle tool path planning method is added in this process to save the machining time and cost collectively. Furthermore, in semi-finish machining, the approximate sub-ruled blade surfaces are calculated, and a new flank milling method of the sub-ruled blade surfaces is achieved; a new solution for tool interference is achieved in this process and the generation of non-interference tool paths becomes easy. Machining experiments of two different impellers are presented as a test of the proposed methods.
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Abdullah, Bestoon, Vadim Varsegov, and Adolf Limansky. "CENTRIFUGAL COMPRESSOR HEAD CHARACTERISTIC OF A MICRO TURBOJET ENGINE BASED ON NUMERICAL SIMULATION." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 62 (2020): 5–11. http://dx.doi.org/10.15593/2224-9982/2020.62.01.
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Shown the possibility of using the standard ANSYS CFX hydrodynamic software package for calculating the gasdynamic characteristics of the centrifugal compressor impeller of micro turbojet engines with different options for profiling blades which based on physical and numerical modeling. Presented a methodology for designing the impeller of a centrifugal compressor based on solving the inverse problem of gas dynamics. As a result of a numerical study, the head coefficient of various forms of the impeller was obtained and presented the dependences of the head coefficient and efficiency on the blade back sweep angle 2 β . b The article discusses the effect of the blade back sweep angle 2 β b on the compressor efficiency and the head characteristic for three different values of the blade back sweep angle 2 β b for example, the impeller with the back sweep angle 2 β b and with the radial blades 2 β 90 b and with blades bent forward 2 β b The centrifugal compressor was designed using Vista CCD programs in one-dimensional computing and Fluid flow CFX in three-dimensional computing. For blade profiling, the BladeGend program was used with different profiling options in order to improve compressor efficiency. The computational grid and the construction of a structured hexahedral mesh for the impeller was carried out in Ansys Turbogrid and the SST model of turbulence was selected in the calculation, which, with sufficient grinding of the mesh at the walls, adequately simulates separated flows at the channel walls, as well as the flow in the flow core. When constructing a grid along the walls between the channel blades, the parameter y + was controlled, which should not exceed 2. It is permissible to use a coarser grid in the flow core compared to the grid near the walls. The design grid of the impeller consists of 350000 elements.
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Luxa, Martin. "The Sonic Surface in the Inter-Blade Channel of the Last Stage Rotor Wheel in the Steam Turbine of Large Output." MATEC Web of Conferences 168 (2018): 02006. http://dx.doi.org/10.1051/matecconf/201816802006.
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The paper deals with sonic surface in a modern turbine wheel consisting of non-prismatic ultra long blades. The whole inter-blade channel is choked. Different positions and shapes of the sonic line in particular cross-sections along the span are observed. The sensitivity of sonic line formation to small changes of effective shape of the inter-blade channel in the root section and the influence of inlet angle, stagger angle and pitch/chord ratio in the tip section are discussed. The problematic of sonic line development in the case of supersonic inlet flow filed is also described. The presented work is based on results of theoretical, experimental and numerical approaches.
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Zhang, Delong, Yu Wang, Junjie Sha, and Yuguang He. "Performance Prediction of a Turbodrill Based on the Properties of the Drilling Fluid." Machines 9, no. 4 (March 31, 2021): 76. http://dx.doi.org/10.3390/machines9040076.
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High-temperature geothermal well resource exploration faces high-temperature and high-pressure environments at the bottom of the hole. The all-metal turbodrill has the advantages of high-temperature resistance and corrosion resistance and has good application prospects. Multistage hydraulic components, consisting of stators and rotors, are the key to the turbodrill. The purpose of this paper is to provide a basis for designing turbodrill blades with high-density drilling fluid under high-temperature conditions. Based on the basic equation of pseudo-fluid two-phase flow and the modified Bernoulli equation, a mathematical model for the coupling of two-phase viscous fluid flow with the turbodrill blade is established. A single-stage blade performance prediction model is proposed and extended to multi-stage blades. A Computational Fluid Dynamics (CFD) model of a 100-stage turbodrill blade channel is established, and the multi-stage blade simulation results for different fluid properties are given. The analysis confirms the influence of fluid viscosity and fluid density on the output performance of the turbodrill. The research results show that compared with the condition of clear water, the high-viscosity and high-density conditions (viscosity 16 mPa∙s, density 1.4 g/cm3) will increase the braking torque of the turbodrill by 24.2%, the peak power by 19.8%, and the pressure drop by 52.1%. The results will be beneficial to the modification of the geometry model of the blade and guide the on-site application of the turbodrill to improve drilling efficiency.
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Zhang, Bo, Quan Hong, Yuanyuan Dou, Honghu Ji, and Rui Chen. "Experimental investigation of flow and heat transfer characteristics on matrix ribbed channel." Thermal Science 24, no. 3 Part A (2020): 1593–600. http://dx.doi.org/10.2298/tsci190702026z.
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The effect of the rib width to height ratio t/e and width to pitch ratio t/p on the local heat transfer distribution in a rectangular matrix ribbed channel with two opposite in line 45? ribs are experimentally investigated for Reynolds numbers from 54000 to 150000. The rib height to channel height ratio e/H is 0.5, t/p and t/e both varies in range of 0.3-0.5. To simulate the actually situation in turbine blades, and provide useful direct results for turbine blade designers, the parameters are same with the blade. The experiments results show that, in comparison to fully developed flow in a smooth pipe of equivalent hydraulic diameter, the Nusselt number inside the matrix-ribbed rectangular channel is increased up to 5 to 9 times higher, while total pressure drop is enlarged by up to significant magnitude. The Nusselt number ratio increases with t/p and t/e increased. Semi-empirical heat transfer is developed for designing of cooling channel.
Dissertations / Theses on the topic "Blade to blade chanel (Intel-blade chanel)"
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Duda, Petr. "Optimalizace polohy propelerové turbíny v kašně." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231499.
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The thesis contains basic information about propeler turbines. It deals with the correct location in the fountain so as to ensure the highest possible performance. Part of the work is devoted to the all-weather resulting blade to blade channels and their impact on the room is filled with diffuser.
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Ricklick, Mark. "CHARACTERIZATION OF AN INLINE ROW IMPINGEMENT CHANNEL FOR TURBINE BLADE COOLING APPLICATIONS." Doctoral diss., University of Central Florida, 2009. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/2696.
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Gas turbines have become an intricate part of today's society. Besides powering practically all 200,000+ passenger aircraft in use today, they are also a predominate form of power generation when coupled with a generator. The fact that they are highly efficient, and capable of large power to weight ratios, makes gas turbines an ideal solution for many power requirement issues faced today. Designers have even been able to develop small, micro-turbines capable of producing efficient portable power. Part of the turbine's success is the fact that their efficiency levels have continuously risen since their introduction in the early 1800's. Along with improvements in our understanding and designs of the aerodynamic components of the turbine, as well as improvements in the areas of material design and combustion control, advances in component cooling techniques have predominantly contributed to this success. This is the result of a simple thermodynamic concept; as the turbine inlet temperature is increased, the overall efficiency of the machine increases as well. Designers have exploited this fact to the extent that modern gas turbines produce rotor inlet temperatures beyond the melting point of the sophisticated materials used within them. This has only been possible through the use of sophisticated cooling techniques, particularly in the 1st stage vanes and blades. Some of the cooling techniques employed today have been internal cooling channels enhanced with various features, film and showerhead cooling, as well as internal impingement cooling scenarios. Impingement cooling has proven to be one of the most capable heat removal processes, and the combination of this cooling feature with that of channel flow, as is done in impingement channel cooling, creates a scenario that has understandably received a great deal of attention in recent years. This study has investigated several of the unpublished characteristics of these impingement channels, including the channel height effects on the performance of the channel side walls, effects of bulk temperature increase on heat transfer coefficients, circumferential heat variation effects, and effects on the uniformity of the heat transfer distribution. The main objectives of this dissertation are to explore the various previously unstudied characteristics of impingement channels, in order to sufficiently predict their performance in a wide range of applications. The potential exists, therefore, for a designer to develop a blade with cooling characteristics specifically tailored to the expected component thermal loads. Temperature sensitive paint (TSP) is one of several non-intrusive optical temperature measurements techniques that have gained a significant amount of popularity in the last decade. By employing the use of TSP, we have the ability to provide very accurate (less than 1 degree Celsius uncertainty), high resolution full-field temperature measurements. This has allowed us to investigate the local heat transfer characteristics of the various channel surfaces under a variety of steady state testing conditions. The comparison of thermal performance and uniformity for each impingement channel configuration then highlights the benefits and disadvantages of various configurations. Through these investigations, it has been shown that the channel side walls provide heat transfer coefficients comparable to those found on the target surface, especially at small impingement heights. Although the side walls suffer from highly non-uniform performance near the start of the channel, the profiles become very uniform as the cross flow develops and becomes a dominating contributor to the heat transfer coefficient. Increases in channel height result in increased non-uniformity in the streamwise direction and decreased heat transfer levels. Bulk temperature increases have also been shown to be an important consideration when investigating surfaces dominated by cross flow heat transfer effects, as enhancements up to 80% in some areas may be computed. Considerations of these bulk temperature changes also allow the determination of the point at which the flow transitions from an impingement dominated regime to one that is dominated by cross flow effects. Finally, circumferential heat variations have proven to have negligible effects on the calculated heat transfer coefficient, with the observed differences in heat transfer coefficient being contributed to the unaccounted variations in channel bulk temperature.Ph.D.
Department of Mechanical, Materials and Aerospace Engineering
Engineering and Computer Science
Mechanical Engineering PhD
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Rupakula, Venkata Panduranga Praveen. "Determination of heat (mass) transfer from blockages with round and elongated holes in a wide rectangular channel." Texas A&M University, 2005. http://hdl.handle.net/1969.1/4977.
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Mass transfer experiments were conducted to study the thermal performance
characteristics of blockages with round and elongated holes, positioned in a 12:1
rectangular channel. Naphthalene sublimation technique was adopted to conduct
experiments with four different blockage configurations, flow rates corresponding to
Reynolds numbers (based on channel hydraulic diameter) of 7,000 and 17,000, and at
three blockage locations. The hole area to channel area ratio for all four blockage
configurations was the same at 0.196. The hole width was half the channel height, and
the distance between consecutive blockages was twice the channel height. Average heat
transfer, local heat (mass) transfer and overall pressure drop results were obtained. The
thermal performance for a particular blockage configuration was measured in terms of
the heat transfer enhancement and the friction factor ratio. Heat transfer enhancement
was measured as a ratio of average Nusselt number on the blockage surface to the
Nusselt number for a thermally fully developed turbulent flow in a smooth channel.
Results indicate that this ratio ranged between 3.6 and 12.4, while the friction factor ratio
varied between 500-1700. The blockage configuration with round holes was found to
yield best thermal performance, while the configuration with largest hole elongation was
nearly equal in thermal performance. In order to compare different blockage
configurations, an average value of upstream and downstream side thermal performances
was used. A general downward trend in Nusselt number ratio with elongation of holes was
observed on the upstream side and a reverse trend was observed on the downstream side.
An upward trend in the Nusselt number ratio with blockage hole elongation on the
downstream side of a blockage was primarily due to jet reversal from the downstream
blockage and its impingement on the downstream surface of the upstream blockage.
Local experiments were performed to compare against the results from average
experiments and also to gain insights into the flow behaviour. There was good
agreement between the results from local and average mass transfer experiments. The
average variation in Nusselt number ratio between local and average mass transfer
experiments was about 5.06%.
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Bhattarai, Kripesh. "On the Use of a Digital Communication Channel for Feedback in a Position Control System." University of Akron / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=akron1353512595.
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Roclawski, Harald. "PIV Measurements of Channel Flow with Multiple Rib Arrangements." UKnowledge, 2001. http://uknowledge.uky.edu/gradschool_theses/303.
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A model of a gas turbine blade cooling channel equipped with turbulators and a backward facing step geometry was examined. Up to four turbulators oriented cross-stream and inclined 45° to the flow direction were mounted in the channel. The blockage ratio b/H of the turbulators and the height h/H of the backward facing step was 0:125 and 0:14 respectively. The number of turbulators as well as their size was varied. In a preliminary investigation, hot-wire and pressure measurements were taken for three different Reynolds numbers (5,000, 12,000, 18,000)in the center plane of the test section. Subsequently, particle image velocimetry (PIV) measurements were made on the same geometries. Results of PIV measurements for a Reynolds number range of Reb=600 to 5,000 for the turbulators and Reh=1,500 to 16,200 for the backward facing step are presented, where Reynolds numbers are based on turbulator height b and step height h, respectively. Plots of the velocity field, vorticity, reverse flow probability and RMS velocity are shown. The focus is on the steady flow behavior but also the unsteadiness of the flow is discussed in one section. Also reattachment lengths were obtained and compared among the various turbulator arrangements and the backward facing step geometry. It was found that the flow becomes periodic after three or four ribs. For one turbulator, a very large separation region was observed. The magnitude of the skin friction factor was found to be the highest for two ribs. If the first rib is replaced by a smaller rib, the skin friction factor becomes the lowest for this case. Compared to the backward facing step, the flow reattaches earlier for multiple turbulators. A dependency of reattachment length on Reynolds number was not observed.
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Jiang, Zhengyi. "Design, development and testing of an automated system for measuring wall thicknesses in turbine blades with cooling channels." Thesis, University of Manchester, 2016. https://www.research.manchester.ac.uk/portal/en/theses/design-development-and-testing-of-an-automated-system-for-measuring-wall-thicknesses-in-turbine-blades-with-cooling-channels(895ac153-e310-40e2-87c6-4e40654c9d5d).html.
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Cooling channels are designed in blades to protect the blades from damage at high temperature in a gas turbine. ELE Advanced Technology Ltd. is a UK company specialised in machining cooling channels in turbine blades using electro-chemical techniques. The wall thicknesses between these cooling channels and the surface of the turbine blade influences the performance of cooling channels and are required to be accurately machined and then inspected. At present, the company measures the wall thicknesses using a hand-held contact ultrasonic probe, which is time-consuming and not very accurate. In this project, an inspection machine has been designed and built for the purpose of automating the procedure of measuring wall thicknesses in turbine blades. The inspection machine measures wall thicknesses based on immersion ultrasonic testing technique and the actuator is a six-axis industrial robot controlled by a computer. Control algorithms have been developed to automate the entire measuring process. Acquired ultrasonic data is also automatically processed using Matlab scripts for wall thickness evaluation. However, prior to the ultrasonic measurement, the probe path has to be calculated. Matlab script has been developed to automatically calculate a probe path using a point cloud of the blade digitized on a CMM as an input. The calculation of the probe path, in general, involves triangulation, parameterisation and B-spline surface approximation. Normal 3D triangulation methods were tested; nevertheless, the results were unsatisfactory. Therefore, a triangulation algorithm is developed based on B-spline curve and 2D Delaunay triangulation. After the probe path is calculated, a localisation method, based on iterative closest point algorithm, is implemented to transform the probe path from CMM to the inspection machine. Several experiments were designed and conducted to study the capability of the ultrasonic probe. Experimental results confirmed the feasibility of using an immersion ultrasonic probe for measuring the wall thicknesses; however, the experiments revealed several limitations of immersion ultrasonic testing, such as the angle of incidence of ultrasonic waves must be maintained within an angular deviation of ±1° from the surface normal to achieve accurate test results. Wall thicknesses of three turbine blades from one batch were measured on the inspection machine. A CT scan image was used as reference to compare the measured wall thicknesses with results obtained using contact probes. The comparison showed the wall thicknesses measured on the inspection machine were much more accurate than using contact probes.
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Nagaiah, Narasimha. "Multiobjective Design Optimization of Gas Turbine Blade with Emphasis on Internal Cooling." Doctoral diss., University of Central Florida, 2012. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/5350.
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In the design of mechanical components, numerical simulations and experimental methods are commonly used for design creation (or modification) and design optimization. However, a major challenge of using simulation and experimental methods is that they are time-consuming and often cost-prohibitive for the designer. In addition, the simultaneous interactions between aerodynamic, thermodynamic and mechanical integrity objectives for a particular component or set of components are difficult to accurately characterize, even with the existing simulation tools and experimental methods. The current research and practice of using numerical simulations and experimental methods do little to address the simultaneous “satisficing” of multiple and often conflicting design objectives that influence the performance and geometry of a component. This is particularly the case for gas turbine systems that involve a large number of complex components with complicated geometries. Numerous experimental and numerical studies have demonstrated success in generating effective designs for mechanical components; however, their focus has been primarily on optimizing a single design objective based on a limited set of design variables and associated values. In this research, a multiobjective design optimization framework to solve a set of user-specified design objective functions for mechanical components is proposed. The framework integrates a numerical simulation and a nature-inspired optimization procedure that iteratively perturbs a set of design variables eventually converging to a set of tradeoff design solutions. In this research, a gas turbine engine system is used as the test application for the proposed framework. More specifically, the optimization of the gas turbine blade internal cooling channel configuration is performed. This test application is quite relevant as gas turbine engines serve a critical role in the design of the next-generation power generation facilities around the world. Furthermore, turbine blades require better cooling techniques to increase their cooling effectiveness to cope with the increase in engine operating temperatures extending the useful life of the blades. The performance of the proposed framework is evaluated via a computational study, where a set of common, real-world design objectives and a set of design variables that directly influence the set of objectives are considered. Specifically, three objectives are considered in this study: (1) cooling channel heat transfer coefficient, which measures the rate of heat transfer and the goal is to maximize this value; (2) cooling channel air pressure drop, where the goal is to minimize this value; and (3) cooling channel geometry, specifically the cooling channel cavity area, where the goal is to maximize this value. These objectives, which are conflicting, directly influence the cooling effectiveness of a gas turbine blade and the material usage in its design. The computational results show the proposed optimization framework is able to generate, evaluate and identify thousands of competitive tradeoff designs in a fraction of the time that it would take designers using the traditional simulation tools and experimental methods commonly used for mechanical component design generation. This is a significant step beyond the current research and applications of design optimization to gas turbine blades, specifically, and to mechanical components, in general.Ph.D.
Doctorate
Industrial Engineering and Management Systems
Engineering and Computer Science
Industrial Engineering
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Waidmann, Christian [Verfasser]. "Heat Transfer Measurements in Rotating Turbine Blade Cooling Channel Configurations using the Transient Thermochromic Liquid Crystal Technique / Christian Waidmann." München : Verlag Dr. Hut, 2021. http://d-nb.info/1232847747/34.
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Liu, Yao-Hsien. "Heat transfer in leading and trailing edge cooling channels of the gas turbine blade under high rotation numbers." [College Station, Tex. : Texas A&M University, 2008. http://hdl.handle.net/1969.1/ETD-TAMU-3196.
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Mhetras, Shantanu. "Experimental study of gas turbine blade film cooling and internal turbulated heat transfer at large Reynolds numbers." [College Station, Tex. : Texas A&M University, 2006. http://hdl.handle.net/1969.1/ETD-TAMU-1820.
Full textBooks on the topic "Blade to blade chanel (Intel-blade chanel)"
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Eisler, Riane Tennenhaus. The chalice andthe blade: Our history, our future. Cambridge, Mass: Harper & Row, 1987.
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2
Gauntt, Randall Owen. The DF-4 fuel damage experiment in ACRR with a BWR control blade and channel box. Washington, DC: Division of Systems Research, Office of Nuclear Regulatory Research, U.S. Nuclear Regulatory Commission, 1989.
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Gauntt, Randall Owen. The DF-4 fuel damage experiment in ACRR with a BWR control blade and channel box. Washington, DC: Division of Systems Research, Office of Nuclear Regulatory Research, U.S. Nuclear Regulatory Commission, 1989.
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4
Eisler, Riane Tennenhaus. The chalice and the blade: Our history, our future. Cambridge [Mass.]: Harper & Row, 1987.
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Eisler, Riane Tennenhaus. The chalice and the blade: Our history, our future. [San Francisco]: HarperCollins, 1988.
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Eisler, Riane Tennenhaus. The chalice and the blade: Our history, our future. [San Francisco, Calif.]: HarperSanFrancisco, 1995.
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The chalice and the blade: Our history, our future. San Francisco: Perennial Library, 1988.
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Freedman, Linda. Continuing Visions. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198813279.003.0011.
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The questions that drove Blake’s American reception, from its earliest moments in the nineteenth century through to the explosion of Blakeanism in the mid-twentieth century, did not disappear. Visions of America continued to be part of Blake’s late twentieth- and early twenty-first century American legacy. This chapter begins with the 1982 film Blade Runner, which was directed by the British Ridley Scott but had an American-authored screenplay and was based on a 1968 American novel, Do Androids Dream of Electric Sheep? It moves to Jim Jarmusch’s 1995 film, Dead Man and Paul Chan’s twenty-first century social activism as part of a protest group called The Friends of William Blake, exploring common themes of democracy, freedom, limit, nationhood, and poetic shape.
Book chapters on the topic "Blade to blade chanel (Intel-blade chanel)"
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Prabhu, A., B. Vasudevan, P. Kailasnath, R. S. Kulkarni, and R. Narasimha. "Blade Manipulators in Channel Flow." In Turbulence Management and Relaminarisation, 97–107. Berlin, Heidelberg: Springer Berlin Heidelberg, 1988. http://dx.doi.org/10.1007/978-3-642-83281-9_7.
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Lu, Long, Vinod Yegneswaran, Phillip Porras, and Wenke Lee. "BLADE: Slashing the Invisible Channel of Drive-by Download Malware." In Lecture Notes in Computer Science, 350–52. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-04342-0_20.
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Sierra-Pérez, Julián, and Joham Alvarez-Montoya. "Strain Field Pattern Recognition for Structural Health Monitoring Applications." In Pattern Recognition Applications in Engineering, 1–40. IGI Global, 2020. http://dx.doi.org/10.4018/978-1-7998-1839-7.ch001.
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Strain field pattern recognition, also known as strain mapping, is a structural health monitoring approach based on strain measurements gathered through a network of sensors (i.e., strain gauges and fiber optic sensors such as FGBs or distributed sensing), data-driven modeling for feature extraction (i.e., PCA, nonlinear PCA, ANNs, etc.), and damage indices and thresholds for decision making (i.e., Q index, T2 scores, and so on). The aim is to study the correlations among strain readouts by means of machine learning techniques rooted in the artificial intelligence field in order to infer some change in the global behavior associated with a damage occurrence. Several case studies of real-world engineering structures both made of metallic and composite materials are presented including a wind turbine blade, a lattice spacecraft structure, a UAV wing section, a UAV aircraft under real flight operation, a concrete structure, and a soil profile prototype.
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Ruse, Michael. "Removing God from Biology." In Science Without God?, 130–47. Oxford University Press, 2019. http://dx.doi.org/10.1093/oso/9780198834588.003.0008.
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The Scientific Revolution changed the root metaphor of science from that of an organism to that of a machine. Mechanism. This meant the expulsion from science of final-cause thinking. For two hundred years, biology resisted this demand. Adaptations like the hand and the eye must be understood in terms of ends. This led Immanuel Kant to state that ‘there will never be a Newton of the blade of grass’. Biology will forever be different, meaning—since the best explanation seems to be divine intervention—God-infused. Charles Darwin challenged this with his mechanism of natural selection, showing that the hand and the eye can be understood in causes of the same nature as those found in the physical sciences. This does not as such refute the existence of God. Moreover, close inspection shows that today’s evolutionary thinking still owes much to its Christian origins.
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Kamboj, Vikram Kumar, Kamalpreet Sandhu, and Shamik Chatterjee. "Modelling Analysis and Simulation for Reliability Prediction for Thermal Power System." In AI Techniques for Reliability Prediction for Electronic Components, 136–63. IGI Global, 2020. http://dx.doi.org/10.4018/978-1-7998-1464-1.ch008.
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The size of the power system is growing exponentially due to heavy demand of power in all the sectors (e.g., agricultural, industrial, and commercial). Due to this, the chance of failure of individual units leading to practical or complete collapse of power supply is common to be encountered. The reliability of power system is therefore the most important feature to be maintained above some acceptable threshold value. Furthermore, the maintenance of individual units can also be planned and implemented once the level of reliability for given instant of time is known. The proposed research therefore aims at determining the threshold reliability of generation system. The generation system consists of boiler, water, blade angle in turbine, shaft coupling, excitation system, generator winding, circuit breaker, and relay. This chapter presents the mathematical model of reliability of individual components and equivalent reliability of the entire generation system. It suggests the approach to determine the critical reliability of both individual and equivalent reliability of the generation system.
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Abdelwahab Elarref, Mohamed, Mogahed Ismail Hassan Hussein, Muhammad Jaffar Khan, and Noran Mohamed Elarif. "Airway Management in Aviation, Space, and Microgravity." In Special Considerations in Human Airway Managements [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.96603.
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Although medical services in aviation have evolved over years based on our understanding of physiology, advancement in monitoring technology but airway management was only recently studied with a focus on space environment. The barometric pressure of ambient air declines as altitude increases, while the volume of air in a confined space will increase according to Boyle law, and therefore oxygen concentration remains at a constant 21%. Altitude sensitive equipment includes endotracheal and tracheostomy cuffs, pneumatic anti shock garments, air splints, colostomy bags, Foley catheters, orogastric and nasogastric tubes, ventilators, invasive monitors, and intra-aortic balloon pumps. The microgravity reduces the body compensation capacity for hemorrhage, while the redistribution of the blood can affect intubation by causing facial edema. Another change is the decreased gastric emptying during aviation. Acute respiratory failure, hypoxemia or inadequate ventilation and protection of the airway in a patient with impaired consciousness are common indications for advanced airway management in aviation. Airway management requires adequate training to maintain excellent medical care during aviation. Tracheal intubation using laryngoscopy would be difficult in microgravity, since the force exerted by the laryngoscope causes the head and neck move out of the field of vision by lever effect exerted on the head and generated through the laryngoscope blade by hand generating a lack of stability, resulting in the difficulty to insert the tracheal tube. While on the ground with the help of gravity, an adequate positioning of the patient is facilitated to achieve alignment of the laryngeal, pharyngeal and oral axes, which is known as sniffing position that allows visualization of the vocal cords and supraglottic structures allowing the introduction of an endotracheal tube.
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deBuys, William. "Janos: A Mirror in Time." In A Great Aridness. Oxford University Press, 2011. http://dx.doi.org/10.1093/oso/9780199778928.003.0009.
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The rains have forsaken El Cuervo for nearly a year, and the mountain-ringed plain that used to be a prairie is as naked as a parking lot. Not a blade of grass is in sight, scarcely a bush. A few low mesquites, defoliated and dormant, hug the parched ground, the wind having packed into their thorny embrace the dried-out stems of last year’s tumbleweeds. Except in the burrows of the kangaroo rats, nothing can be hidden here. A lost coin or key would shout its presence, much as the potsherds do on the mounds of the ancient pueblo by the arroyo. Every edible thing has been consumed, every plant nipped off at the level of the ground. Even the soil is leaving, blown away, tons to the acre, by winds that sweep down from the Sierra Madre, a dozen miles to the west. If you were to make your way to the top of one of the chipped-tooth peaks of the sierra (no small task), you would be able to look down into great canyons. One of those canyons belongs to the Río Gavilán, where in 1936 Aldo Leopold glimpsed a kind of ecological heaven that no longer exists. From atop the peak you would also see for great distances, certainly as far as Janos, the crossroads and market town through which nearly every visitor to this northwest corner of Chihuahua passes, and on a dustless day you might see the gritty penumbra of Ciudad Juárez and El Paso, far on the northeastern horizon. The air is dry, and here it is empty of pollution, which makes El Cuervo and its environs a good place for looking long distances, even into the past. One way to understand changes in the land is to visit a place that shows how things used to be. That’s what Leopold realized when he visited the Río Gavilán. He saw it as a fragment of the Southwest that had escaped the pressures of white settlement, and he recognized it as a mirror of how Arizona and New Mexico used to be, back in the days when the Apaches still roamed their homeland in freedom.
Conference papers on the topic "Blade to blade chanel (Intel-blade chanel)"
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Zhang, Q., L. He, and A. Rawlinson. "Effects of Inlet Turbulence and End-Wall Boundary Layer on Aero-Thermal Performance of a Transonic Turbine Blade Tip." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2019.
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Most of previous researches of inlet turbulence effects on blade tip have been carried out for low speed situations. Recent work has indicated that for a transonic turbine tip, turbulent diffusion tends to have distinctively different impact on tip heat transfer than for its subsonic counterpart. It is hence of interest to examine how inlet turbulence flow conditioning would affect heat transfer characteristics for a transonic tip. This present work is aimed to identify and understand the effects of both inlet freestream turbulence and end-wall boundary layer on a transonic turbine blade tip aero-thermal performance. Spatially-resolved heat transfer data are obtained at aerodynamic conditions representative of a high-pressure turbine, using the transient infrared thermography technique with the Oxford High-Speed Linear Cascade research facility. With and without turbulence grids, the turbulence levels achieved are 7–9% and 1% respectively. On the blade tip surface, no apparent change in heat transfer was observed with high and low turbulence intensity levels investigated. On the blade suction surface, however, substantially different local heat transfer for the suction side near tip surface have been observed, indicating a strong local dependence of the local vortical flow on the freestream turbulence. These experimentally observed trends have also been confirmed by CFD predictions using Rolls-Royce HYDRA. Further CFD analysis suggests that the level of inflow turbulence alters the balance between the passage vortex associated secondary flow and the OverTL flow. Consequently, enhanced inertia of near wall fluid at a higher inflow turbulence weakens the cross-passage flow. As such, the weaker passage vortex leads the tip leakage vortex to move further into the mid passage, with the less spanwise coverage on the suction surface, as consistently indicated by the heat transfer signature. Different inlet end-wall boundary layer profiles are employed in the HYDRA numerical study. All CFD results indicate the inlet boundary layer thickness has little impact on the heat transfer over the tip surface as well as the pressure side near-tip surface. However, noticeable changes in heat transfer are observed for the suction side near-tip surface. Similar to the freestream turbulence effect, such changes are attributed to the interaction between the passage vortex and the OTL flow.
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Coull, John D., and Nicholas R. Atkins. "The Influence of Boundary Conditions on Tip Leakage Flow." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2057.
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Most of the current understanding of tip leakage flows has been derived from detailed cascade experiments. However, the cascade model is inherently approximate since it is difficult to simulate the boundary conditions present in a real machine, particularly the secondary flows convecting from the upstream stator row and the relative motion of the casing and blade. This problem is further complicated when considering the high pressure turbine rotors of aero engines, where the high Mach numbers must also be matched in order to correctly model the aerodynamics and heat transfer. More realistic tests can be performed on high-speed turbines, but the experimental fidelity and resolution achievable in such set-ups is limited. In order to examine the differences between cascade models and real-engine behavior, the influence of boundary conditions on the tip leakage flow in an unshrouded high pressure turbine rotor is investigated using RANS calculations. This study examines the influence of the rotor inlet condition and relative casing motion. A baseline calculation with a simplified inlet condition and no relative endwall motion exhibits similar behavior to cascade studies. Only minor changes to the leakage flow are induced by introducing either a more realistic inlet condition or relative casing motion. However when both of these conditions are applied simultaneously the pattern of leakage flow is very different, with ingestion of flow over much of the early suction surface. The paper explores the physical processes driving this change and the impact on leakage losses and modeling requirements.
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Rademaker, Edward R., Rob A. Huls, Bambang I. Soemarwoto, and Ron van Gestel. "Modeling Approach to Calculate Redistributions of HPT-Shroud Cooling Channels Minimizing Thermal Stresses Including Some Turbine Blade Tip Effects." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2060.
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A numerical case study on a HPT-shroud of a medium-sized commercial engine has been carried out to investigate the heat loading and the possible redistribution (number of channels, position and exit angle) of shroud cooling channels facing the turbine blade tip. A combination of modeling vehicles was used to quantify the aerodynamics, the thermodynamics and resulting heat loads on the shroud. This includes a 1-D gas turbine performance simulation model, engineering models for cooling flow distributions and heat loads, CFD modeling of the HPT flow including some tip flow effects and the finite element modeling to calculate the temperature and stress distribution in the solid shroud. Regions with high temperatures and/or maximum thermal stresses and the potential for reduction by relocating the cooling channels at equal amounts of cooling flow were identified. Although the physics involved in the processes is much more complicated than modeled, the parametric studies gave valuable insight and quantitative results in terms of differences in shroud temperatures and thermal stresses. A complementary experimental study on shroud maintenance and service experiences (not published yet) has delivered data for model input support and comparison with the numerical results.
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Biester, Marc H. O., Dimitri Karapetrow, and Joerg R. Seume. "Effect of the Tip Clearance on End Wall Heat-Transfer in a HP Turbine." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2069.
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The present investigation analyzes the effect of the extension of the radial gap on the heat transfer at the blade tip and the casing within a high-pressure turbine stage of an aircraft engine. Due to the rotation and the interaction of the adjacent blade-rows, the flow field in the tip region of an unshrouded rotor-blade is characterized by a high level of unsteadiness. Furthermore, the casing is exposed to the passing blade-gap and corresponding changes in the velocity-profile, the resulting near-wall velocity-gradients, and the resulting changes in heat transfer. In order to account for these effects, time-resolved RANS computations of three different radial gaps are performed and evaluated. The present analysis shows an influence of the radial gap on the characteristics of the steady and unsteady heat transfer and a correlation with the size of the tip-clearance vortex can be shown.
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Granovskiy, Andrey, Igor Manaev, Vladimir Vassiliev, and Harald Kissel. "Effects of Blade Degradation on Turbine Performance." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2039.
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The degradation of gas turbine parts due to aging leads to changes in airfoil shape and often causes performance loss. Although the degradation mechanisms and their effects on performance are understood in general (e.g. it is well known that fouling of compressor airfoils reduces mass flow and efficiency), the first quantitative relationships between specific types of part degradation and performance characteristics have only recently been published. In this paper the degradation of turbine blades with aft-loaded airfoils is considered. The typical deviations of shape were identified based on field experience. The effects of these deviations on turbine performance were assessed using different calculation methods, including 3D Navier-Stokes calculations and methods based on empirical correlations. The effect of blades-length reduction, chord-length reduction, changes in trailing-edge thickness and shape, and variation of stagger angle were analysed. The analysis showed that for aft-loaded airfoils without shrouds, the major influence on turbine performance is the degradation of radial clearances. A simplified engineering procedure allowing estimation of turbine performance loss due to degradation has been developed. This paper demonstrates how this simplified procedure, can be applied to the estimation of turbine recovery potential during a typical engine overhaul.
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Benoni, Albert, and Reinhard Willinger. "Design Modification of a Passive Tip-Leakage Control Method for Axial Turbines: Linear Cascade Wind Tunnel Results." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2056.
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Tip-leakage losses can contribute up to one third of the overall losses in unshrouded axial turbine blades. A passive tip-leakage flow control method is used to reduce the tip-leakage loss. Taking into account a modified discharge coefficient model, an inclination of the injection against the tip-leakage flow direction is said to have an even better effect on reducing the tip-leakage loss. To prove the effect, linear cascade measurements have been carried out at three different gap widths from 0.85% to 2.50% chord length. The used geometry is an up-scaled turbine blade tip cross section with weak turning. A single blade is fitted with an injection channel which is inclined by 45° against the tip-leakage flow direction. The flow field of the modified blade was measured 0.31 axial chord length downstream of the cascade using a pneumatic five-hole probe. The tip-leakage loss is reduced by passive tip-injection and further by inclined injection. The reduction can be significant at small gap widths. Detailed results are presented for a gap width of 1.40% chord length.
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Virdi, A. S., Q. Zhang, L. He, H. D. Li, and R. Hunsley. "Aerothermal Performance of Shroudless Turbine Blade Tips With Effects of Relative Casing Motion." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2021.
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Recent work has indicated qualitatively different heat transfer characteristics between a transonic blade tip and a subsonic one. High resolution experimental data can be acquired for blade tip heat transfer research using a high speed linear cascade. While recognising an important role played by the cascade tests in validating computational models at the same conditions, some questions arise in relation to the effects of relative casing motion: 1) Does the relative casing movement change the main flow physics influencing the blade tip aerothermal performance? 2) Can a cascade set up with stationary casing wall rank different designs? 3) How do the effects of the casing motion depend on tip design configurations? A combined experimental and CFD study on several high pressure blade tip configurations is conducted to address these issues. Firstly, extensive experimental tests with aerodynamic loss and heat transfer measurement in a high speed linear cascade have been carried out for a squealer tip configuration at engine representative aerodynamic conditions. A systematic validation of the CFD solver (Rolls-Royce HYDRA) is presented, which serves as a basis for the computational analyses of the effects of the relative casing motion. Two tip configurations (squealer and flat tip) at three tip gaps (0.5%, 1.0%, 1.5% span) are analysed. The main aerodynamic impact of the casing motion is seen to promote the passage vortex, which consequently supresses the pitchwise reach of the tip leakage vortex. Inside the tip gap, the behaviour is dominated by the extra wall friction in relation of the inertia of the bulk fluid through the gap. As such, the moving casing effect is particularly strong for the flat tip at a small tip gap. For the large and medium tip gaps, both stationary and moving casing results are shown to consistently capture the trends in overall aerothermal performances. The present results confirm that even with relative casing motion, there is still a significant portion of transonic flow over a blade tip. For both the stationary and moving casing cases, the gap dependence of the over-tip heat transfer shows opposite trends for the transonic and subsonic regions respectively. The gap dependence of the blade tip heat transfer is shown to be clearly dependent on tip geometry configurations, as the bulk flow in a squealer cavity is subsonic regardless of the tip gap size, whilst the local flow state over a flat tip is much more responsive to the change of gap size.
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Ledezma, G. A., J. Allen, and R. S. Bunker. "An Experimental and Numerical Investigation Into the Effects of Squealer Blade Tip Modifications on Aerodynamic Performance." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2004.
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Gas turbine blades using the so-called squealer tip configuration represent a majority of the high-pressure first stage blades in service. The squealer tip in its most basic format is simply a two-tooth labyrinth seal projecting from the blade tip towards the stationary shroud or casing. As with all blade tip configurations, the geometry is a compromise between aerodynamics, cooling, mechanical stress, durability, and repair. While many proposed blade tip innovations involve more complex geometries, this study seeks to determine if a simpler geometry, other than a flat tip, can provide equivalent aerodynamic performance with a reasonable chance of satisfying all other design factors. Using an annular sector blade cascade, total pressure loss surveys are measured with three blade tip geometries, the standard squealer tip, a single-sided suction side seal strip, and the single-sided strip with a pressure side winglet added. The same cascade is modeled numerically as a periodic passage for each of the geometries tested. Experiment and simulation both utilize all blade tip cooling flow injection locations and nominal magnitudes, as well as a constant tip clearance above the suction side seal strip. Experimental data show that the removal of the pressure side seal strip reduces the area-averaged total pressure loss slightly, while the addition of a winglet returns the performance to the baseline result. Numerical predictions indicate essentially equal performance for all geometries. The numerical results provide insight into the loss mechanisms of both the tip leakage flows and the coolant injection flows. This study, when combined with literature data on heat transfer and cooling, concludes that the simpler single-sided suction seal strip is better overall than the commonly employed squealer tip.
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Tikhonov, Aleksei S., Andrey A. Shvyrev, and Nikolay Yu Samokhvalov. "Turbine Split Rings Thermal Design Using Conjugate Numerical Simulation." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2003.
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One of the key factors ensuring gas turbine engines (GTE) competitiveness is improvement of life, reliability and fuel efficiency. However fuel efficiency improvement and the required increase of turbine inlet gas temperature (T*g) can result in gas turbine engine life reduction because of hot path components structural properties deterioration. Considering circumferential nonuniformity, local gas temperature T*g can reach 2500 K. Under these conditions the largest attention at designing is paid to reliable cooling of turbine vanes and blades. At present in design practice and scientific publications comparatively little attention is paid to detailed study of turbine split rings thermal condition. At the same time the experience of modern GTE operation shows high possibility of defects occurrence in turbine 1st stage split ring. This work objective is to perform conjugate numerical simulation (gas dynamics + heat transfer) of thermal condition for the turbine 1st stage split ring in a modern GTE. This research main task is to determine the split ring thermal condition by defining the conjugate gas dynamics and heat transfer result in ANSYS CFX 13.0 package. The research subject is the turbine 1st stage split ring. The split ring was simulated together with the cavity of cooling air supply from vanes through the case. Besides turbine 1st stage vanes and blades have been simulated. Patterns of total temperature (T*Max = 2000 °C) and pressure and turbulence level at vanes inlet (19.2 %) have been defined based on results of calculating the 1st stage vanes together with the combustor. The obtained results of numerical simulation are well coherent with various experimental studies (measurements of static pressure and temperature in supply cavity, metallography). Based on the obtained performance of the split ring cooling system and its thermal condition, the split ring design has been considerably modified (one supply cavity has been split into separate cavities, the number and arrangement of perforation holes have been changed etc.). All these made it possible to reduce considerably (by 40…50 °C) the split ring temperature comparing with the initial design. The design practice has been added with the methods which make it possible to define thermal condition of GTE turbine components by conjugating gas dynamics and heat transfer problems and this fact will allow to improve the designing level substantially and to consider the influence of different factors on aerodynamics and thermal state of turbine components in an integrated programming and computing suite.
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Mamaev, B. I., M. M. Petukhovsky, and A. V. Pozdnyakov. "Shrouding the First Blade of High Temperature Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2001.
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Blade shrouding gives an opportunity to increase the HPT (high pressure turbine) first stage efficiency by 2–3 %. However, if high gas temperature and high circumferential velocity are at the stage, shrouding can be problematic due to load increasing at blade/disk attachment and high temperature of the shroud itself. To make blade/disk attachment more reliable the shroud axial width has to be decreased by increasing a relative pitch of airfoil cascades t (t = t / b, where t – pitch, b – chord) at the blade tip span. According to experience for a flow with β1 = 50 – 85°, M2 = 0.8 – 1, and Re = (0.8 – 1)•106 high efficient cascades with t = 0.93 – 1.05 can be designed. Application of such a profiling for GTE (gas turbine engine) turbine is demonstrated here. In the turbine meridian flow path the blade was drastically tapered to the tip (tip width was 53 % of the mean width and 46 % of the hub width). To lighten the blade a partial shrouding can be also applied. Model turbine tests showed that local cuts at the front shroud area and the aft shroud area at the airfoil pressure side influenced the efficiency weakly. Required shroud temperature is provided with a cooling. The aircraft turbine with a governed cooling system and a radial clearance control is an example here. In this case the shroud had 3 labyrinth ribs. The shrouding decreased radial clearance by 0.8 mm at main design modes that increased efficiency by ∼ 1.5 %. To cool down the shroud the air downstream the compressor was fed into the cavity behind the front labyrinth rib. At maximal mode with full cooling the relative coolant mass flow (to the compressor mass flow) was mc = 1.3 % and gas leakages through the labyrinth were 0.2 %. It gave acceptable mixed temperature of 530°C in the cavity over the shroud. At cruise high altitude mode and a lower gas temperature and partial cooling with mc = 0.4 % and gas leakages of 0.1 % the mixed temperature also did not exceed 530°C over the shroud. The assessment with taking into account changes of the clearance, the coolant mass flow, and gas leakages showed that the shrouding provided the engine economy improvement by 0.7 – 0.9 % for both modes. For GTPU (gas turbine power unit) the first blade shrouding can be more complicated. However, even the slight turbine efficiency increase provides considerable profits due to GTPU huge power output and long term running. So, when GTE and GTPU designing starts, it is reasonable to consider the turbine first blade shrouding. Here the integral evaluation criterion, which includes the assessment of a possible income from the unit full life cycle running, has to be applied.
Reports on the topic "Blade to blade chanel (Intel-blade chanel)"
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Singh, Gyanender, Jacob P. Gorton, Danny Schappel, Benjamin S. Collins, Nicholas R. Brown, and Brian D. Wirth. Impact of Control Blade Insertion on the Deformation Behavior of SiC-SiC Channel Boxes in Boiling Water Reactors. Office of Scientific and Technical Information (OSTI), October 2019. http://dx.doi.org/10.2172/1615808.
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Gauntt, R., R. Gasser, and L. Ott. The DF-4 fuel damage experiment in ACRR (Annual Core Research Reactor) with a BWR (Boiling Water Reactor) control blade and channel box. Office of Scientific and Technical Information (OSTI), November 1989. http://dx.doi.org/10.2172/5101359.
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