Relevant bibliographies by topics / Turbine blade development

Academic literature on the topic 'Turbine blade development'

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Published: 6 September 2023

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Journal articles on the topic "Turbine blade development"

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Han, Je-Chin, and Srinath Ekkad. "Recent Development in Turbine Blade Film Cooling." International Journal of Rotating Machinery 7, no. 1 (2001): 21–40. http://dx.doi.org/10.1155/s1023621x01000033.

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Gas turbines are extensively used for aircraft propulsion, land-based power generation, and industrial applications. Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperature (RIT). The current RIT level in advanced gas turbines is far above the .melting point of the blade material. Therefore, along with high temperature material development, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. Gas turbine blades are cooled internally and externally. This paper focuses on external blade cooling or so-called film cooling. In film cooling, relatively cool air is injected from the inside of the blade to the outside surface which forms a protective layer between the blade surface and hot gas streams. Performance of film cooling primarily depends on the coolant to mainstream pressure ratio, temperature ratio, and film hole location and geometry under representative engine flow conditions. In the past number of years there has been considerable progress in turbine film cooling research and this paper is limited to review a few selected publications to reflect recent development in turbine blade film cooling.
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Alipour, Ramin, Roozbeh Alipour, Seyed Saeid Rahimian Koloor, Michal Petrů, and Seyed Alireza Ghazanfari. "On the Performance of Small-Scale Horizontal Axis Tidal Current Turbines. Part 1: One Single Turbine." Sustainability 12, no. 15 (July 24, 2020): 5985. http://dx.doi.org/10.3390/su12155985.

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The blade number of a current tidal turbine is one of the essential parameters to increase the stability, performance and efficiency for converting tidal current energy into rotational energy to generate electricity. This research attempts to investigate the effect of blade number on the performance of a small-scale horizontal tidal current turbine in the case of torque, thrust coefficient and power coefficient. Towards this end and according to the blade element momentum theory, three different turbines, i.e., two, three and four-bladed, were modeled using Solidworks software based on S-814 airfoil and then exported to the ANSYS-FLUENT for computational flow dynamics (CFD) analysis. SST-K-ω turbulence model was used to predict the turbulence behavior and several simulations were conducted at 2 ≤ tip speed ratio ≤ 7. Pressure contours, turbulence kinetic energy contours, cut-in-speed-curves, and streamlines around the blades and rotors were extracted and compared to provide an ability for a deep discussion on the turbine performance. The results show that in the case of obtainable power, the optimal value of tip speed ratio is around 5, so that the maximum power was achieved for the four-bladed turbine. Out of optimal condition, higher blade number and lower blade number turbines should be used at less than and greater than the optimal values of tip speed ratio, respectively. The results of simulations for the three-bladed turbine were validated against the experimental data with good agreement.
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Anderson, Benjamin, Pietro Bortolotti, and Nick Johnson. "Development of an open-source segmented blade design tool." Journal of Physics: Conference Series 2265, no. 3 (May 1, 2022): 032023. http://dx.doi.org/10.1088/1742-6596/2265/3/032023.

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Abstract As wind turbines continue to grow ever larger to reduce the cost of energy, their blades follow suit, with the largest commercial offshore blades extending past 100 m. Massive blades such as these raise key transportation and manufacturing challenges, especially for land-based turbines. Segmented blades are one solution and are garnering increased industry and research interest. In this work, a detailed mechanical joint model is integrated into the Wind-Plant Integrated System Design and Engineering Model (WISDEM®), which will facilitate future segmented blade research and optimization. WISDEM is used to design a wind turbine with 100-m segmented blades. This wind turbine design is compared to other machines with 100-m monolithic blades designed for rail-transportability. The designs are compared in terms of blade mass and cost, turbine capital cost, annual energy production, and levelized cost of energy, with monolithic designs being the lightest and most economical. However, this result may vary by wind plant location. A variety of segmentation joint types exist, and they will inevitably vary in parameters such as cost, spanwise location, and physical characteristics. This work examines the sensitivity of wind turbine design drivers and annual energy production to a variety of the aforementioned parameters, using the open-source wind turbine design codes OpenFAST and WISDEM, finding that joint mass, stiffness, and location can have significant effects on design drivers.
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Pandey, Rohit. "Development and Optimization of Wind Turbine Blade Design for Enhanced Efficiency." Mathematical Statistician and Engineering Applications 70, no. 1 (January 31, 2021): 519–26. http://dx.doi.org/10.17762/msea.v70i1.2505.

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The improvement and optimisation of wind energy system performance and efficiency depend heavily on the design of wind turbine blades. Wind power has emerged as a viable option for environmentally friendly electricity generation in response to the rising demand for renewable energy sources. The structural properties and aerodynamic performance of a wind turbine's blades have a significant impact on its efficiency.This study focuses on the systematic creation and efficiency optimisation of wind turbine blade designs. The study uses a multidisciplinary strategy that incorporates optimisation, structural analysis, and aerodynamics. The goal is to increase power generation while maintaining the structural integrity, cost-effectiveness, and safety of the blades.The research starts with a thorough examination of the strengths and weaknesses of the current designs for wind turbine blades. To assess the performance of various blade shapes, various aerodynamic theories, computational fluid dynamics (CFD) simulations, and wind tunnel measurements are used. The issue of wind turbine blade noise is also included in the study. To lessen the influence of noise on the environment, noise reduction techniques like trailing-edge serrations are being researched. The project also investigates the use of cutting-edge materials, like carbon fibre composites, to lighten the blades without sacrificing their structural integrity.The results of this study are anticipated to have a big impact on wind turbine blade design. It is projected that the optimised blade designs will improve wind energy systems' overall efficiency by boosting power output and lowering aerodynamic loads. While the use of noise reduction measures enhances the environmental friendliness of wind turbines, structural analysis ensures the safety and dependability of the blades.
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Finnegan, William, Priya Dasan Keeryadath, Rónán Ó Coistealbha, Tomas Flanagan, Michael Flanagan, and Jamie Goggins. "Development of a numerical model of a novel leading edge protection component for wind turbine blades." Wind Energy Science 5, no. 4 (November 13, 2020): 1567–77. http://dx.doi.org/10.5194/wes-5-1567-2020.

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Abstract. As the world shifts to using renewable sources of energy, wind energy has been established as one of the leading forms of renewable energy. However, as wind turbines get increasingly larger, new challenges within the design, manufacture and operation of the turbine are presented. One such challenge is leading edge erosion on wind turbine blades. With larger wind turbine blades, tip speeds begin to reach over 300 km h−1. As water droplets impact along the leading edge of the blade, rain erosion begins to occur, increasing maintenance costs and reducing the design life of the blade. In response to this, a new leading edge protection component (LEP) for offshore for wind turbine blades is being developed, which is manufactured from thermoplastic polyurethane. In this paper, an advanced finite element analysis (FEA) model of this new leading edge protection component has been developed. Within this study, the FEA model has been validated against experimental trials at demonstrator level, comparing the deflection and strains during testing, and was found to be in good agreement. The model is then applied to a full-scale wind turbine blade and is then modelled with the LEP bonded onto the blade's leading edge and compared to previously performed experimental trials, where the results were found to be well aligned when comparing the deflections of the blade. The methodology used to develop the FEA model can be applied to other wind blade designs in order to incorporate the new leading edge protection component to eliminate the risk of rain erosion and improve the sustainability of wind turbine blade manufacture while increasing the service life of the blade.
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Boedi, Silvy Dollorossa, Josephine Sundah, Meidy Kawulur, and Franklin Bawano. "Design and Construction of Kinetic Turbine External Hinged Blade as A Picohydro Scale Power Plant." International Journal of Innovative Technology and Exploring Engineering 12, no. 1 (December 30, 2022): 43–47. http://dx.doi.org/10.35940/ijitee.a9367.1212122.

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The problem of energy shortage is still a global problem which is especially felt in developing countries whose residents live in villages, which still require the development of more efficient energy sources. Limited fossil fuels make water energy the best energy option. The problem of meeting the availability of electricity in rural areas by utilizing water energy as new and renewable energy is a long-term goal in this research. The current research on kinetic turbines is a combination of two types of waterwheels, which have a vertical axis (overshot and swell turbines). The vertical shaft is made so that the generator is easier to install and all the blades get a boost in the flow of water. Most water turbines have fixed blades. In this research, the target of the novelty is a kinetic turbine with a vertical shaft which has a hinged blade. Hinged blades are blades that can move when the flow of water hits the blades, so that on one side of the turbine it will reduce the negative torque and on the other hand it will increase the rotation of the turbine. The results of the research that became the target, namely, obtained a turbine design that has more optimal turbine power and efficiency, compared to a turbine that has a fixed blade, so that this externally hinged blade kinetic turbine can contribute to the provision of rural electrical energy. This research method is an experiment by doing independent variations on the number of blades, and blade 10 has an optimum power value of 59.01 Watt.
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Rantererung, Corvis L., Titus Tandiseno, and Mika Mallisa. "Development of Four Nossel Cross Flow Turbine." Journal of Physics: Conference Series 2394, no. 1 (December 1, 2022): 012029. http://dx.doi.org/10.1088/1742-6596/2394/1/012029.

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Abstract ross flow turbines are widely used as turbines for driving micro-scale hydropower plants in rural areas, but their efficiency is still low because cross flow turbines only use one nozzle. The utilization of the potential energy of water is not optimal yet to be converted into pressure and kinetic energy of water in the nozzles with high water velocity hitting the turbine blades. The problem of cross flow turbines with one nozzle has an uneven flow of water to the turbine blades, and it is not effective in converting potential energy into power in the turbine. The purpose of this research is to develop a four-nozzle Cross Flow turbine and test its performance. The method used is to conduct experimental testing in a laboratory that tests the performance of a cross flow turbine using four nozzles. A cross flow turbine with four nozzles has better performance than a cross flow turbine using only one nozzle. The results obtained that the cross flow turbine with four nozzles where the water jets out of the nozzle is more evenly distributed and the flow of water enters the turbine blade runner, resulting in a good impulse reaction in the blades. The conclusion is that the performance of the four nozzle cross flow turbine is able to produce higher turbine rotation, power and efficiency.
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Zawadzki, Karol, Wojciech Śmiechowicz, Małgorzata Stępień, Anna Baszczyńska, and Michał Tarkowski. "Influence of the Solidity Ratio on the Small Wind Turbine Aerodynamics." E3S Web of Conferences 242 (2021): 03006. http://dx.doi.org/10.1051/e3sconf/202124203006.

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Increasing popularity of individualised electricity generation from wind by prosumers creates a strong demand for profitable and highly efficient small wind turbines. This paper investigates the influence of rotor blade solidity parameter on device efficiency in hope of determining its optimal value as a part of the development process of the GUST small wind turbine. The study involved experimental analysis in the wind tunnel and numerical simulations performed in QBlade software. Different solidities of the rotor were achieved by alteration of (1) number of blades and (2) chord distribution along the blade span. The increase of rotor solidity resulted in augmentation of the aerodynamic efficiency in both approaches. The elongation of the chord by 33% in a 3-bladed rotor resulted in a bigger power coefficient increment than addition of a 4th blade with original chord distribution. Even though the solidity was the same, the 3-bladed rotor performed better, possibly due to lower form drag. The results emphasize the importance of the rotor solidity optimization during the small wind turbine rotor development and may significantly influence overall power output.
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Xu, Liang, Zineng Sun, Qicheng Ruan, Lei Xi, Jianmin Gao, and Yunlong Li. "Development Trend of Cooling Technology for Turbine Blades at Super-High Temperature of above 2000 K." Energies 16, no. 2 (January 5, 2023): 668. http://dx.doi.org/10.3390/en16020668.

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Aeroengines and heavy-duty gas turbines are the core power equipment in the field of national defense and energy. Their research and development (R&D) level and manufacturing level represent the status of a country’s heavy industry in the world. The common cooling technologies of turbine blades including impingement cooling, film cooling, effusion cooling, layer cooling, pin fin cooling, and rough ribs were introduced in this paper. With the continuous improvement of the efficiency and performance of aeroengines and gas turbines, the turbine inlet temperature increases gradually every year; turbine blades will be exposed to higher gas temperatures in the future as gas temperatures break 2000 K. In order to ensure the safe operation of turbine blades under severe super-high temperature working conditions, cooling technology must be developed emphatically. This paper first reviews the research status of turbine blade cooling technology and points out future research focuses. The development trends of next-generation turbine blade cooling technology for above 2000 K temperature are summarized from several aspects: the innovative excavation of high-efficiency composite cooling configuration, multi-objective cooperative cooling structure and optimization design based on 3D printing, composite cooling structure design and optimization based on an artificial intelligence algorithm, tapping the cooling potential of new cooling media and heat pipes, integrated thermal protection with new thermal insulators, and the application of low-resistance and high-efficiency surface dimple cooling. The summary of this paper can provide a reference for the researchers of turbine blade cooling technology.
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Sutrisno, Sutrisno, Deendarlianto Deendarlianto, Indarto Indarto, Sigit Iswahyudi, Muhammad Agung Bramantya, and Setyawan Bekti Wibowo. "Performances and Stall Delays of Three Dimensional Wind Turbine Blade Plate-Models with Helicopter-Like Propeller Blade Tips." Modern Applied Science 11, no. 10 (September 30, 2017): 189. http://dx.doi.org/10.5539/mas.v11n10p189.

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The research on three dimensional (3-D) wind turbine blades has been introduced (Sutrisno, Prajitno, Purnomo, & B.W. Setyawan, 2016). In the current experiment, the 3-D wind turbine blades would be fitted with helicopter-like blade tips and additional fins to the blade hubs to demonstrate some laminarizing features. It was found that additional helicopter-like blade tip to the turbine blade creates strong laminar flows over the surface of the blade tips. Supplementary, finned hub, fitted to the blade body, creates rolled-up vortex flows, weakens the blade stall growth development, especially for blades at high-speed wind. A proposed mathematical form of modified lifting line model has been developed to pursue further 3-d blade development study of 3-d wind turbine blade. Rolled up vortex effects, developed by finned of the base hub, has been acknowledged could demolish the turbulent region, as well as laminarize the stall domain to intensify the induced wind turbine blade lift.
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Dissertations / Theses on the topic "Turbine blade development"

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Jousselin, Olivier. "Development of blade tip timing techniques in turbo machinery." Thesis, University of Manchester, 2013. https://www.research.manchester.ac.uk/portal/en/theses/development-of-blade-tip-timing-techniques-in-turbo-machinery(da682144-7009-4cdc-8f52-ff7cd0cf1cf1).html.

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In the current gas turbine market, the traditional design-test-redesign loop is not a viable solution to deploy new products within short timeframes. Hence, to keep the amount of testing to an absolute minimum, theoretical simulation tools like Finite Element Modelling (FEM) have become a driving force in the design of blades to predict the dynamic behaviour of compressor and turbine assemblies in high-speed and unsteady flows. The predictions from these simulation tools need to be supported and validated by measurements. For the past five years, Rolls-Royce Blade Tip Timing (BTT) technology has been replacing rotating Strain Gauge systems to measure the vibration of compressor blades, reducing development times and costs of new aero engine programmes. The overall aim of the present thesis is to progress the BTT technology to be applied to aero engine turbine modules. To this end, the two main objectives of this project are: i. To improve the current validated Rolls-Royce BTT extraction techniques, through the development of novel algorithms for single/multiple asynchronous and responses. ii. To validate the improved extraction using simulated and real engine test data in order to bring the Turbine BTT technology to a Rolls-Royce Technology Readiness Level (TRL) of 4 (i.e. component and/or partial system validation in laboratory environment). The methodology adopted for the development of the novel algorithms is entirely based on matrix algebra and makes extensive use of singular value decomposition as a means for assessing the degree optimisation achieved through various novel manipulations of the input (probe) raw data. The principle contributions of this thesis are threefold: i. The development of new BTT matrix-based models for single/multiple non-integral and integral engine order responses that removed certain pre-processing assumptions required by the current method. ii. The development of BTT technology to operate under the constraint of having equally spaced probes, which is unavoidable in turbines and renders current BTT methods unusable for turbine applications. iii. The development of methods for extracting measurement uncertainty and signal to noise ratios that are based solely on the raw data, without reliance on simulated reference data. Following the verification and validation of the new processing algorithms against simulated data and against validated software with numerous examples of actual engine test data, a Rolls-Royce's Research & Technology (R&T) Critical Capability Acquisition and Capability Readiness (CCAR) review has accredited the novel techniques with a TRL of 4.
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Caraballo, Torrealba Edgar Jesus. "Modeling and Control Development for a Turbine Blade Testing Facility." Miami University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=miami1574434292454319.

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Gorle, Jagan Mohan Rao. "Development of Circulation Controlled Blade Pitching Laws for Low-Velocity Darrieus Turbine." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2015. http://www.theses.fr/2015ESMA0021/document.

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L'étude développée dans cette thèse concerne le contrôle des performances et des lâchers tourbillonnaires au cours du cycle de rotation d'une hydrolienne à axe vertical de type Darrieus. L'élaboration d'une famille de lois de commande d'incidence de pales exploitant le principe de conservation de la circulation autour de profils en mouvement permet ici le contrôle du fonctionnement de l'hydrolienne ainsi que la maîtrise de son sillage tourbillonnaire afin de préserver l'environnement.L'écoulement 2D est simulé à l'aide du solveur incompressible de Star CCM+ afin de mettre en évidence l'effet de ce type de contrôle sur le rendement de la turbine pour différents points de fonctionnement. Ce modèle CFD a été utilisé pour améliorer l'analyse analytique en ce qui concerne l'extraction de l'énergie, la compréhension de l'écoulement autour de l'hydrolienne et le contrôle des tourbillons générés. La nouveauté de cette étude est l'élaboration de lois de commande de pales d'hydrolienne, basées sur des valeurs constantes et transitoires de la circulation, afin d'augmenter la puissance de la turbine tout en garantissant un contrôle efficace de la vorticité et ainsi prévenir de l'interaction entre les tourbillons et les pales. Une bonne comparaison est réalisée entre les résultats analytiques et numériques concernant les forces hydrodynamiques.En outre, une campagne d'essais a été menée afin d'acquérir des mesures quantitatives sur une hydrolienne de type Darrieus à pales fixes en terme de puissance, mais aussi des résultats qualitatifs pertinents comme la visualisation de l'écoulement autour des pales à différentes positions et pour différents points de fonctionnement. La mise en place complète d'un système PTV pour les mesures qualitatives et les étapes de traitement sont discutées et les divers paramètres obtenus à partir des études CFD sont validées en utilisant ces résultats PIV.L'étude expérimentale dans la présente recherche appo11e des informations détaillées sur les gradients de pression et de vitesse, les contours de vorticité et le critère Q qui ont servi à valider les visualisations obtenues numériquement
With key applications in marine renewable energy. the vertical axis water turbine can use current or tidal energy in an eco-friendly manner. However, it is difficult to reconcile optimal performance of hydrokinetic turbines and compliance wilh the aquatic environment as the main drawback of the turbines is the formation of non-linear flow structures caused by the unsteady movement of the blades. Eddies in the flow are advected and can interact with other blades, which leads to a reduction in power output. To limit this phenomenon, the turbines operate at high speeds, which are likely to reduce the shaft power. High speeds of rotational so forbid the passage of aquatic animais, and are the cause of a suction effect on the sediments.The objective of this thesis work is twofold. First, it aims to develop a blade pitch control to get the flow adjusted around the blade profile at any given flow configuration by incorporatin.g the profile's motion with respect to incident flow. Such a system intends to achieve the objective of operating at reduced speeds without vortical releases, which should allow achieving a high torque without causing damage to the environment.This thesis work is mainly carried out in three phases. ln the first phase, the irrotational flow over an arbitrary profile is formulated using conforma] mapping. Prospective potential flow application on the basis of Couchet theory (1976) is involved in the development of a control law that decides the blade pitching in a constant circulation framework. In the second phase, a numerical validation of the developed analytical work is presented using CFD to examine how the theoretical fomulation can be effectively applied to Darricus turbines. In the final phase, two prototypes are developed, one is classical Darrieus turbine with fixed blades, and other is the turbine with pitching blades for experimental measurements of performance as well as flow fields(by PIV) in order to validate the computational results
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Bai, Qian. "Development of a new process to reduce distortion in gas turbine blade forging." Thesis, Imperial College London, 2012. http://hdl.handle.net/10044/1/39131.

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The aim of this study is to develop a new process for high precision hot forging of Ti-6Al-4V gas turbine blade. In this new process, the work-piece is hot formed and then is clamped between the dies at high pressure for a certain time in order to decrease the distortion and increase the geometric accuracy. The feasibility study of the new process has been carried out in this thesis by using experiments and finite element (FE) modelling, providing a scientific understanding of the process. From the experimental and modelling work, it has been demonstrated that the new process proposed in this thesis is an effective way to reduce distortion in gas turbine blade forging. The study can be divided into three parts: interfacial heat transfer coefficient determination, material modelling, and Ti-6Al-4V hot forming. A closed form method to determine an interfacial heat transfer coefficient (IHTC) was developed, and a one-dimensional heat transfer model was proposed and validated. Heat transfer tests were performed to study the heat transfer between Ti-6Al-4V work-pieces with an initial temperature of 920°C and H13 dies with an initial temperature of 150°C. Temperature histories measured by thermocouples were obtained, and were used as an input for the closed form method. The effects of pressure, glaze thickness and surface roughness on IHTC between Ti-6Al-4V work-pieces and H13 steel dies were studied. Thermo-mechanical properties of Ti-6Al-4V were investigated for a temperature range of 820°C to 1120°C and a strain rate range of 0.1s-1 to 10.0s-1, using a Gleeble thermo-mechanical simulator. The flow softening mechanisms of Ti-6Al-4V during hot forming were studied. A set of unified elastic-viscoplastic constitutive equations for Ti-6Al-4V during hot forming were developed. Plastic strain for alpha and beta phase, isotropic hardening, normalised dislocation density, adiabatic heating, phase transformation, and globularisation of alpha phase were described in the set of constitutive equations. The developed material constitutive model was determined by fitting with experimental strain-stress curves from uniaxial compression tests, using an Evolutionary Programming (EP)-based optimisation method. Good agreements between the experimental and computed results were obtained: the error of predicted stress is under 10%. The general trend exhibited by softening mechanism of Ti-6Al-4V during hot forging is correctly fitted. Hot forming tests were conducted to study the effects on distortion during hot forming strips used as analogous to gas turbine blades. The effect of work-piece thickness and holding time on spring-back were investigated. The unified constitutive equations for Ti-6Al-4V and IHTCs were integrated with commercial FE software DEFORM/2D to simulate material flow and heat transfer in the hot forming process. The FE model was validated by experimental results. A good agreement was obtained between experimental and FE results for temperature history and thickness distribution. The stress state, temperature field and phase volume fraction were obtained from FE simulation. The FE model can be used to predict the extent of distortion in an appropriate FE software, and thus to optimise the new hot forging process for Ti-6Al-4V high precision gas turbine blade.
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Cigeroglu, Ender. "Development of microslip friction models and forced response prediction methods for frictionally constrained turbine blades." Columbus, Ohio : Ohio State University, 2007. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1181856489.

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Guo, Shengmin. "Heat transfer and aerodynamic studies of a nozzle guide vane and the development of new heat transfer gauges." Thesis, University of Oxford, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.389217.

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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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Lynch, Stephen P. "The Effect of Endwall Contouring On Boundary Layer Development in a Turbine Blade Passage." Diss., Virginia Tech, 2011. http://hdl.handle.net/10919/77202.

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Increased efficiency and durability of gas turbine components is driven by demands for reduced fuel consumption and increased reliability in aircraft and power generation applications. The complex flow near the endwall of an axial gas turbine has been identified as a significant contributing factor to aerodynamic loss and increased part temperatures. Three-dimensional (non-axisymmetric) contouring of the endwall surface has been shown to reduce aerodynamic losses, but the effect of the contouring on endwall heat transfer is not well understood. This research focused on understanding the general flow physics of contouring and the sensitivity of the contouring to perturbations arising from leakage features present in an engine. Two scaled low-speed cascades were designed for spatially-resolved measurements of endwall heat transfer and film cooling. One cascade was intended for flat and contoured endwall studies without considering typical engine leakage features. The other cascade modeled the gaps present between a stator and rotor and between adjacent blades on a wheel, in addition to the non-axisymmetric endwall contouring. Comparisons between a flat and contoured endwall showed that the contour increased endwall heat transfer and increased turbulence in the forward portion of the passage due to displacement of the horseshoe vortex. However, the contour decreased heat transfer further into the passage, particularly in regions of high heat transfer, due to delayed development of the passage vortex and reduced boundary layer skew. Realistic leakage features such as the stator-rotor rim seal had a significant effect on the endwall heat transfer, although leakage flow from the rim seal only affected the horseshoe vortex. The contours studied were not effective at reducing the impact of secondary flows on endwall heat transfer and loss when realistic leakage features were also considered. The most significant factor in loss generation and high levels of endwall heat transfer was the presence of a platform gap between adjacent airfoils.
Ph. D.
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Sahay, Prateek. "Development of a Robotic Cell for Removal of Tabs from Jet Engine Turbine Blade." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1574417686354007.

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ALINEJAD, FARHAD. "Development of advanced criteria for blade root design and optimization." Doctoral thesis, Politecnico di Torino, 2018. http://hdl.handle.net/11583/2711560.

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In gas and steam turbine engines, blade root attachments are considered as critical components which require special attention for design. The traditional method of root design required high experienced engineers yet the strength of the material was not fully exploited in most cases. In the current thesis, different methodologies for automatic design and optimization of the blade root has been evaluated. Moreover, some methods for reducing the computational time have been proposed. First, a simplified analytical model of the fir-tree was developed in order to evaluate mean stress in different sections of the blade root and disc groove. Then, a more detailed two-dimensional shape of the attachment capable to be analyzed in finite element (FE) analysis was developed for dovetail and fir-tree. The model was developed to be general in a way to include all possible shapes of the attachment. Then the projection of the analytical model over the 2D model was performed to compare the results obtained from analytical and FE methods. This comparison is essential in the later use of analytical evaluation of the fir-tree as a reduction technique of searching domain optimization. Moreover, the possibility of predicting the contact normal stress of the blade and disc attachment by the use of a punch test was evaluated. A puncher composed of a flat surface and rounded edge was simulated equivalent to a sample case of a dovetail. The stress profile of the contact in analytical, 2d and 3d for puncher and dovetail was compared. As an optimizer Genetic Algorithm (GA) was described and different rules affecting this algorithm was introduced. In order to reduce the number of callbacks to high fidelity finite element (FE) method, the surrogate functions were evaluated and among them, the Kriging function was selected to be constructed for use in the current study. Its efficiency was evaluated within a numerical optimization of a single lob. In this study, the surrogate model is not used solely in finding the optimum of the attachment shape as it may provide low accuracy but in order to benefit its fast evaluation and diminish its low accuracy drawback, the Kriging function (KRG) was used within GA as a pre-evaluation of the candidate before performing FE analysis. Moreover, the feasible and non-feasible space in a multi-dimensional complex searching domain of the attachment geometry is explained and also the challenge of a multi-district domain is tackled with a new mutation operation. In order to rectify the non-continuous domain, an adaptive penalty method based on Latin Hypercube Sampling (LHS) was proposed which could successfully improve the optimization convergence. Furthermore, different topologies of the contact in a dovetail were assessed. Four different types of contact were modeled and optimized under the same loading and boundary conditions. The punch test was also assessed with different contact shapes. In addition, the state of stress for the dovetail in different rotational speed with different types of contact was assessed. In the results and discussion, an optimization of a dovetail with the analytical approach was performed and the optimum was compared with the one obtained by FE analysis. It was found that the analytical approach has the advantage of fast evaluation and if constraints are well defined the results are comparable to the FE solution. Then, a Kriging function was embedded within the GA optimization and the approach was evaluated in an optimization of a dovetail. The results revealed that the low computational cost of the surrogate model is an advantage and the low accuracy would be diminished in a collaboration of FE and surrogate models. Later, the capability of employing the analytical approach in a fir-tree optimization is assessed. As the fir-tree geometry has a higher complexity working domain in comparison to the dovetail, the results would be consistent for the dovetail also. Different methods are assessed and compared. In the first attempt, the analytical approach was adopted as a filter to select out the least probable fit candidates. This method could provide a 7\% improvement in convergence. In another attempt, the proposed adaptive penalty method was added to the optimization which successfully found the reasonable optimum with 47\% reduction in computational cost. Later, a combination of analytical and FE models was joined in a multi-objective multi-level optimization which provided 32\% improvement with less error comparing to the previous method. In the last evaluation of this type, the analytical approach was solely used in a multi-objective optimization in which the results were selected according to an FE evaluation of most fit candidates. This approach although provided 86\% improvement in computational time reduction but it depends highly on the case under investigation and provides low accuracy in the final solution. Furthermore, a robust optimum was found for both dovetail and fir-tree in a multi-objective optimization. In this trial, the proposed adaptive penalty method in addition to the surrogate model was also involved.
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Books on the topic "Turbine blade development"

1

A, Cyr M., Strange R. R, and United States. National Aeronautics and Space Administration., eds. Turbine blade and vane heat flux sensor development phase 2. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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A, Cyr M., Strange R. R, and United States. National Aeronautics and Space Administration, eds. Turbine blade and vane heat flux sensor development phase 2. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Barnard, Mark C. S. Pistons to blades: Small gas turbine developments by the Rover Company. Derby: Rolls-Royce Heritage Trust, 2003.

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Lane, Christopher. The Development of a 2D Ultrasonic Array Inspection for Single Crystal Turbine Blades. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-02517-9.

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Chandrashekar, S. Technology & innovation in China: A case study of single crystal superalloy development for aircraft turbine blades. Bangalore: International Strategic & Security Studies Programme, National Institute of Advanced Studies, 2011.

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Alloy Design Challenge: Development of Low Density Superalloys for Turbine Blade Applications. Independently Published, 2020.

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Lane, Christopher. Development of a 2D Ultrasonic Array Inspection for Single Crystal Turbine Blades. Springer, 2013.

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Lane, Christopher. The Development of a 2D Ultrasonic Array Inspection for Single Crystal Turbine Blades. Springer, 2016.

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Lane, Christopher. The Development of a 2D Ultrasonic Array Inspection for Single Crystal Turbine Blades. Springer, 2013.

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Book chapters on the topic "Turbine blade development"

1

Abo-Serie, Essam, and Elif Oran. "Flow Simulation of a New Horizontal Axis Wind Turbine with Multiple Blades for Low Wind Speed." In Springer Proceedings in Energy, 93–106. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-30960-1_10.

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AbstractIn this paper, a new design of a small horizontal-axis wind turbine is introduced. The design is based on the authors’ patent, which uses permanent magnets impeded into a shroud that holds the rotor blades. The generator coils are installed on a fixed diffuser that houses the rotor and acts as a wind concentrator. Therefore, the new design has no hub and is based on direct coupling for electricity generation. The main features of the design have been explored to highlight the advantages with a focus on how the new design can be integrated with the recent development of green buildings. The effect of increasing the number of blades and blade chord distribution on turbine performance has been investigated for the new turbine. Initial design and analysis were carried out using the Blade Element Momentum method and CFD simulations to identify the turbine performance and examine the flow characteristics. The results showed that further energy can be extracted from the turbine if the blade chord size increases at the shroud location and reduces at the turbine hub for a low Tip Speed Ratio TSR within the range of 1.5–3. Furthermore, having more blades can significantly increase the power coefficient and extend the range of operation with a high power coefficient. The number of blades, however, has to be optimised to achieve maximum power relative to the cost. Adding a diffuser and flanges surrounding the turbine can further increase the energy extracted from the wind at low speed.
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Šabić, Muharem, Edvin Šimić, and Said Šabić. "Analysis and Choice of Gas Turbine Blade." In New Technologies, Development and Application VI, 29–35. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-34721-4_4.

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Amano, Ryoichi S. "Aerodynamic Behavior of Rear-Tubercle Horizontal Axis Wind Turbine Blade." In Sustainable Development for Energy, Power, and Propulsion, 545–62. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5667-8_22.

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Elatife, Khalid, and Abdellatif El Marjani. "Blade Profile Effect on the Impulse Radial Turbine Performances for OWC Wave Energy Converter." In International Conference on Advanced Intelligent Systems for Sustainable Development, 149–61. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-35245-4_14.

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de Oliveira, A. R., A. B. da Rocha, E. da T. Marcelino, R. I. Lopes, J. V. de M. Rodrigues, and R. N. C. Duarte. "Development of a Wind Turbine Blade with Dedicated Profiles by Schmitz’s Optimum Dimensioning Systematization." In Mechanisms and Machine Science, 544–59. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-99272-3_38.

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Rame, J., P. Caron, D. Locq, O. Lavigne, L. Mataveli Suave, V. Jaquet, M. Perrut, J. Delautre, A. Saboundji, and J. Y. Guedou. "Development of AGAT, a Third-Generation Nickel-Based Superalloy for Single Crystal Turbine Blade Applications." In Superalloys 2020, 31–40. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-51834-9_3.

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Potluri, Sri Shanti, Shyam Kishore, R. Isai Thamizh, and B. V. A. Patnaik. "Development of Reduced Order Strain Model for Life Assessment of a Gas Turbine Rotor Blade." In Lecture Notes in Mechanical Engineering, 97–106. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-4779-9_8.

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Joy Mathavan, J., and Amar Patnaik. "Development and Characterization of Polyamide Fiber Composite Filled with Fly Ash for Wind Turbine Blade." In Lecture Notes in Mechanical Engineering, 131–39. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-32-9931-3_14.

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Ngala, G. M., and M. Shuwa. "Development of a Micro Horizontal Axis Wind Turbine Blade for the Semi-Arid Region of Nigeria." In Innovative Renewable Energy, 681–91. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-76221-6_75.

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Klötzer, Christian, Martin-Christoph Wanner, Wilko Flügge, and Lars Greitsch. "Implementation of Innovative Manufacturing Technologies in Foundries for Large-Volume Components." In Annals of Scientific Society for Assembly, Handling and Industrial Robotics 2021, 229–40. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-74032-0_19.

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AbstractThe development of new manufacturing technologies opens up new perspectives for the production of propellers (diameter < 5 m), especially since the use of the established sand casting process as a technology is only partially competitive in today’s market. Therefore, different applications of generative manufacturing methods for the implementation into the production process were investigated. One approach is the mould production using additive manufacturing processes. Investigations showed that especially for large components with high wall thicknesses available systems and processes for sand casting mould production are cost-intensive and conditionally suitable. With our development of a large-format FDM printer, however, the direct production of large-format positive moulds for, for example, yacht propellers up to 4 m in diameter is possible. Due to the comparatively low accuracy requirements for the mould, the focus is on the durability of the drive system and the rigidity of this FDM printer. Equipped with simple linear technology in portal design and cubic design of the frame structure with rigid heated print bed, the aim is to achieve maximum material extrusion via the print head. The production of plastic models not only facilitates handling during the moulding process, but also allows considerable time and cost savings to be made during the running process. A further step in our development is the direct production of the components using WAAM. A possible concept for robot-supported build-up welding for the production of new innovative propeller geometries is presented using the example of a hollow turbine blade for a tidal power plant.
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Conference papers on the topic "Turbine blade development"

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Scrinzi, Erica, Iacopo Giovannetti, Nuo Sheng, and Luc Leblanc. "Development of New Abradable/Abrasive Sealing Systems for Clearance Control in Gas Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2065.

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Abradable/abrasive sealing systems are currently used in gas turbines to reduce the blade tip gas leakage and consequently improve the turbine efficiency. The coatings selection is directly related to the section in which they are used. Seal systems for hot gas paths are primarily required to withstand high temperature. The abradable coating should be easily removed by the tip blade without causing significant blade wear, whereas the blades should have sufficient cutting capabilities. Durability properties, such as erosion resistance, are also required. Owing to their temperature capabilities, porous ceramic coatings are successfully used as abradable coatings. Although they are characterized by good abradability properties, their resistance to environmental attacks, such as solid particle erosion, is limited by the porous microstructure which negatively affects their service life. It is apparent that durability and abradability are the main targets to be simultaneously achieved for ensuring longer service life and improved efficiency. The present work is aimed at developing new abradable/abrasive coatings pairs able to ensure both the durability performances of the coatings and good abradability properties. Three ceramic abradable coatings with DVC and porous microstructure have been studied. The down-selection process has been carried out by considering the microstructure, the hardness, the tensile adhesion strength, the erosion resistance, and the furnace cycle test resistance. A composite coating made by NiCoCrAlY matrix containing abrasive grits applied by electrolytic process was selected as abrasive material system. The abrasive grits (patent application in process by GE Oil&Gas) consists of a mixture of ceramic particles. These grits ensure both short-term cutting capability and thermal stability, assuring the clearance maintenance over time. The abradability of the seal system was assessed by a properly designed test, namely Rub Rig test, which simulates the blade incursion in the abradable coating. Surface patterns on abradable coating were also considered to further enhance the abradability. Engine tests are foreseen for assessing the service behavior of this seal system.
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SUAREZ, E., and H. PRZIREMBEL. "Pyrometry for turbine blade development." In 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3036.

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Wagner, L. F., and J. H. Griffin. "Blade Vibration With Nonlinear Tip Constraint: Model Development." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-293.

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Turbine blades having integrally-machined tip shrouds, with associated gaps between adjacent shrouds, often exhibit unusual vibratory responses with significant differences between the amplitudes and frequencies of individual blades on the same stage. These differences result from unavoidable variations in the shroud gaps causing, for large enough excitation, nonlinear constraint at the blade tips which varies from blade to blade. This study shows that the blade stresses cannot be adequately represented by the type of single degree-of-freedom models that are often used for dynamic impact studies, but require the participation of higher frequency beam-type modes. The extension of the resulting beam model to multi-degree-of-freedom systems will allow the study of the “gap mistuning” phenomenon for practical bladed disks.
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Bright, Eric, Roger Burleson, Steve A. Dynan, and William T. Collins. "NT164 Silicon Nitride Gas-Turbine Engine Turbine Blade Manufacturing Development." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-074.

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Norton Advanced Ceramics (NAC) has performed ceramic turbine blade fabrication development as part of several DOD and DOE-sponsored programs including: (1) The Experimental Turbine Engine Concept (ETEC); (2) The Advanced Turbine Technology Applications Project (ATTAP); (3) The Ceramic Turbine Engine Development Project (CTEDP); and (4) The Ceramic Stationary Gas Turbine (CSGT). NAC has developed two HIPed silicon nitide materials for fabricating turbine blades within these programs — One is designated NT154; and the second is designated NT164. Under the ETEC program with AlliedSignal Engines, NT154 blades were fabricated and delivered for proof and engine testing. Blade fabrication development efforts were augmented by NAC’s work under the ATTAP, which was directed at developing manufacturing technologies for rotors, stators, scrolls, vanes, and other components. Under the ATTAP, complex-shape forming was emphasized utilizing pressure slip-casting. NAC has employed pressure slip casting developed under the ATTAP to fabricate ceramic turbine blades and other gas-turbine components for various advanced heat-engine efforts. NT154 nozzles have been delivered to AlliedSignal Engines under internally sponsored and DOD-sponsored programs. NT154 diffusers, nozzles, and monorotors have been delivered to Sundstrand Power Systems. Under the CTEDP and CSGT programs, continued efforts on turbine blade fabrication development are anticipated for 1995 and beyond. Work under the CTEDP program with AlliedSignal Engines is focused on cost reduction through process simplification and scale-up. Under the CSGT program, NAC is participating with Solar Turbines Incorporated to deliver prototype quantities of NT164 silicon nitride blades using a controlled fabrication process. NAC is utilizing its prior experience in fabricating similar blade geometries under the ETEC, ATTAP, and CTEDP programs in the CSGT effort.
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Gebhard, Susanne, Tanja Wobst, Dan Roth-Fagaraseanu, and Matthew Hancock. "Advanced Coating Systems for Future Shroudless Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2017.

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Shroudless turbine designs offer the advantages of weight reduction and lower mechanical loads on the one hand but bear challenges as high gap sensitivity and high temperatures of the static parts on the other hand. In the last years, a lot of work was carried out in order to develop a sealing system for a shroudless design consisting of an abrasive blade tip coating and an abradable segment coating addressing all the requirements defined. Aside from being abradable, the segment coatings have to be mechanically stable, withstand high thermo-mechanical loadings and have to work for thicknesses larger than 1 mm. Due to the limited temperature capability of the currently used segment coating material yttria-stabilised zirconia, which combines advantageously a suitable thermal conductivity with a high thermal expansion coefficient, new ceramic materials for the segment coating had to be developed. A very promising sealing system combines an abrasive blade tip coating with an yttria-stabilised zirconia / magnesia alumina spinel double-layer abradable coating system with a 3D interface structure between the bond coat and the ceramic coatings. The present work gives an overview of the development and the performance of this sealing system.
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Wheeler, Andrew P. S., and Richard D. Sandberg. "Direct Numerical Simulations of a Transonic Tip Flow With Free-Stream Disturbances." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2037.

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In this paper we use direct numerical simulation to investigate the unsteady flow over a model turbine blade-tip at engine scale Reynolds and Mach numbers. The DNS is performed with a new in-house multi-block structured compressible Navier-Stokes solver purposely developed for exploiting high-performance computing systems. The particular case of a transonic tip flow is studied since previous work has suggested compressibility has an important influence on the turbulent nature of the separation bubble at the inlet to the gap and subsequent flow reattachment. The effects of free-stream turbulence, cross-flow and pressure-side boundary-layer on the tip flow aerodynamics and heat transfer are investigated. For ‘clean’ in-flow cases we find that even at engine scale Reynolds numbers the tip flow is intermittent in nature (neither laminar nor fully turbulent). The breakdown to turbulence occurs through the development of spanwise modes with wavelengths around 25% of the gap height. Cross-flows of 25% of the streamwise gap exit velocity are found to increase the stability of the tip flow, and to significantly reduce the turbulence production in the separation bubble. This is predicted through in-house linear stability analysis, and confirmed by the DNS. For the case when the inlet flow has free-stream turbulence, viscous dissipation and the rapid acceleration of the flow at the inlet to the tip-gap causes significant distortion of the vorticity field and reductions of turbulence intensity as the flow enters the tip gap. This means that only very high turbulence levels at the inlet to the computational domain significantly affect the tip heat transfer. The DNS results are compared with RANS predictions using the Spalart-Allmaras and k–ω SST turbulence models. The RANS and DNS predictions give similar qualitative features for the tip flow, but the size and shape of the inlet separation bubble and shock positions differ noticeably. The RANS predictions are particularly insensitive to free-stream turbulence.
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Curtis, E. M., H. P. Hodson, M. R. Banieghbal, J. D. Denton, R. J. Howell, and N. W. Harvey. "Development of Blade Profiles for Low Pressure Turbine Applications." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-358.

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This paper describes a programme of work, largely experimental, which was undertaken with the objective of developing an improved blade profile for the low-pressure turbine in aero-engine applications. Preliminary experiments were conducted using a novel technique. An existing cascade of datum blades was modified to enable the pressure distribution on the suction surface of one of the blades to be altered. Various means, such as shaped inserts, an adjustable flap at the trailing edge, and changing stagger were employed to change the geometry of the passage. These experiments provided boundary layer and lift data for a wide range of suction surface pressure distributions. The data was then used as a guide for the development of new blade profiles. The new blade profiles were then investigated in a low-speed cascade that included a set of moving bars upstream of the cascade of blades 10 simulate the effect of the incoming wakes from the previous blade row in a multistage turbine environment. Results are presented for two improved profiles that are compared with a datum representative of current practice. The experimental results include loss measurements by wake traverse, surface pressure distributions, and boundary layer measurements. The cascades were operated over a Reynolds Number range from 0.7 × 105 to 4.0 × 105. The first profile is a “laminar flow” design that was intended to improve the efficiency at the same loading as the datum. The other is a more highly loaded blade profile intended to permit a reduction in blade numbers. The more highly loaded profile is the most promising candidate for inclusion in future designs. It enables blade numbers to be reduced by 20%, without incurring any efficiency penalty. The results also indicate that unsteady effects must be taken into consideration when selecting a blade profile for the low-pressure turbine.
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Rajendran, Nanthini, Bhamidi Prasad, and Y. V. S. S. Sanyasiraju. "Development of Turbine Blade Profiles Using Iterative Inverse Design Methodology." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4553.

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An iterative inverse design methodology is used to design gas turbine blades for the prescribed flow conditions. The input flow parameter considered here is the pressure distribution along the suction and pressure surfaces of the blade. The flow is regarded as inviscid. A guess blade is presumed and the flow analysis over the blade is determined using the existing commercial software. In case of mismatch of the flow parameters, the guessed profile surface is considered as a permeable membrane and the normal velocity on the blade surface is computed by conservation of momentum flux approach. The computed normal velocity is used to revise the blade geometry by mass conservation principle till the flow parameters converge. A few geometric constraints are enforced on the model to avoid quixotic blade model. The validation of the above method is being done using NACA profiles. The robustness of the method is verified by using various combinations of NACA blade profiles, where different initial guessed profiles are taken for the same prescribed pressure distribution. This approach can be extended to three dimensional cases. To incorporate the complications attached with the three dimensional flows, three two dimensional sections can be considered on the blade geometry namely at hub, mid span and tip.
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9

Landry, C., P. K. Dubois, N. Courtois, F. Charron, M. Picard, and J. S. Plante. "Development of an Inside-Out Ceramic Turbine." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57041.

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Ceramic turbines could substantially increase operating temperatures of turbomachinery without the need of blade cooling, leading to higher conversion efficiency and power density. However, the inherent brittleness and low tensile strength of ceramic materials limits the use of hub-based ceramic turbines. This paper presents a novel inside-out turbine architecture, permitting the use of monolithic ceramic blades. The proposed architecture uses a carbon-polymer composite rim which converts the rotor radial loads to tangential hoop stress. The blades mainly support compressive loads, minimizing tensile stresses within the blade and thus crack propagation. This allows the use of low tensile strength ceramics which cannot be used in standard hub-based turbines. The rotor hub is comprised of two radially flexible C-shaped hubs, which have sufficient compliance to follow radial displacement of the heavily loaded composite rim. The feasibility of the proposed inside-out ceramic turbine is demonstrated by addressing the four key challenges of the architecture using proof-of-concept prototypes, namely: (1) rotor dynamics of the flexible hub; (2) thermal viability of the composite rim (3) local tensile stress in the blades, and (4) thermal shock in the ceramic blades in transient mode. Experimental validation with an alumina blade confirms that this architecture supports the use of low tensile strength, brittle ceramic blades.
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Pechlivanoglou, G., G. Weinzierl, I. T. Masmanidis, C. N. Nayeri, T. P. Philippidis, and C. O. Paschereit. "Utilization of Modern Large Scale HAWT Blade Design Techniques for the Development of Small HAWT Blades." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25309.

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Lately the need for modern medium capacity wind turbines for self-consumption within urban and rural areas has risen again. The great majority however of the large wind turbine manufacturers are not interested in this small profit market. SMART BLADE GmbH in cooperation with the CORE Team of the University of Patras have decided to develop modern, sophisticated rotor blades with state of the art tools from the multi-MW wind turbine industry in order to boost the development of the upcoming modern small capacity wind turbines. The current paper presents the design of a modern 4m wind turbine blade with optimal aerodynamic design aimed at a variable speed hybrid stall operation.
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Reports on the topic "Turbine blade development"

1

Wright, David M., and DOE Project Officer - Keith Bennett. Low Speed Technology for Small Turbine Development Reaction Injection Molded 7.5 Meter Wind Turbine Blade. Office of Scientific and Technical Information (OSTI), July 2007. http://dx.doi.org/10.2172/921599.

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Gogolewski, R. P., and B. J. Cunningham. Terminal ballistic experiments for the development of turbine engine blade containment technology. Office of Scientific and Technical Information (OSTI), January 1995. http://dx.doi.org/10.2172/87317.

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Ely, George Ray, Dennis P. Roach, Thomas M. Rice, Garrett Dean Nelson, and Joshua Paquette. Development and Evaluation of a Drone-Deployed Wind Turbine Blade Nondestructive Inspection System. Office of Scientific and Technical Information (OSTI), March 2018. http://dx.doi.org/10.2172/1528806.

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Hughes, Scott. Wind Turbine Blade Test Definition of the DeWind DW90 Rotor Blade: Cooperative Research and Development Final Report, CRADA Number CRD-09-326. Office of Scientific and Technical Information (OSTI), May 2012. http://dx.doi.org/10.2172/1040941.

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Francis A. Di Bella. Development of a Wave Energy -Responsive Self-Actuated Blade Articulation Mechanism for an OWC Turbine. Office of Scientific and Technical Information (OSTI), June 2010. http://dx.doi.org/10.2172/1054197.

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Hughes, Scott. NREL Wind Turbine Blade Structural Testing of the Modular Wind Energy MW45 Blade: Cooperative Research and Development Final Report, CRADA Number CRD-09-354. Office of Scientific and Technical Information (OSTI), May 2012. http://dx.doi.org/10.2172/1040946.

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Amarendra K. Rai. DEVELOPMENT OF PROTECTIVE COATINGS FOR SINGLE CRYSTAL TURBINE BLADES. Office of Scientific and Technical Information (OSTI), December 2006. http://dx.doi.org/10.2172/895828.

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Snowberg, David, Derek Berry, Dana Swan, Zhang Mingfu, Steve Nolet, Douglas Adams, Johnathan Goodsell, Dayakar Penumadu, and Aaron Stebner. IACMI Project 4.2: Thermoplastic Composite Development for Wind Turbine Blades. Office of Scientific and Technical Information (OSTI), December 2021. http://dx.doi.org/10.2172/1834393.

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Mascarenas, David. Development of Event-Based Data Acquisition for Acoustic Emission Monitoring of the Structural Integrity of Wind Turbine Blades. Office of Scientific and Technical Information (OSTI), July 2023. http://dx.doi.org/10.2172/1993187.

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Wind Turbine Blade Fatigue Analysis for Development of Predictive Life Models: Cooperative Research and Development Final Report, CRADA Number CRD-17-00696. Office of Scientific and Technical Information (OSTI), September 2020. http://dx.doi.org/10.2172/1665832.

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