Relevant bibliographies by topics / Turbine disk

Academic literature on the topic 'Turbine disk'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Turbine disk"

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Vinnes, Magnus K., Stefano Gambuzza, Bharathram Ganapathisubramani, and R. Jason Hearst. "The far wake of porous disks and a model wind turbine: Similarities and differences assessed by hot-wire anemometry." Journal of Renewable and Sustainable Energy 14, no. 2 (March 2022): 023304. http://dx.doi.org/10.1063/5.0074218.

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The wakes of two different porous disks have been evaluated experimentally. Such disks are commonly used as physical actuator disk analogs for wind turbines. One disk is made of a uniform wire mesh, while the other has a nonuniform design with radial spars connected by rings. The disks have the same solidity and produce approximately the same drag. The wakes have also been compared to the wake of a model wind turbine and a solid disk. In contrast to earlier studies, the far wake, up to 30 diameters downstream, is included in the comparison. In the near wake, the velocity deficit and turbulence intensity profiles of the disk wakes differ significantly. High levels of turbulence intensity in the wake of the nonuniform disk increase the transverse transport in the wake, which leads to faster spreading and lower velocity deficits in the far wake, compared to the uniform disk and the wind turbine. High velocity gradients in the wake of the uniform disk give rise to turbulence production farther downstream, maintaining higher turbulence levels in the far wake. In addition, coherent vortex shedding is only identified in the wake of the nonuniform disk. None of the disks were able to replicate the asymmetric features of the wind turbine wake. Nonetheless, the results highlight important flow physics that should be considered in the design process of a porous disk used as a wind turbine surrogate.
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Hamdani Umar, Teuku Muhammad Kashogi, Sarwo Edhy Sofyan, Razali Thaib, and Akram. "CFD Simulation of Tesla Turbines Performance Driven by Flue Gas of Internal Combustion Engine." Journal of Advanced Research in Applied Mechanics 98, no. 1 (October 15, 2022): 1–11. http://dx.doi.org/10.37934/aram.98.1.111.

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The reduced production of fossil energy, especially petroleum, has encouraged researchers to continuously increase the role of new and renewable energy as part of energy security and independence. A Tesla turbine is a device that can be used to recover wasted energy from exhaust gases, thereby increasing the overall energy use. The purpose of this study was to assess the performance of a Tesla turbine using various parameters such as engine speed, the gap between the disks, the diameter of the disks, and the number of disks. In this study, the performance of a Tesla turbine was simulated using computational fluid dynamics (CFD). The reference dimensions of this Tesla turbine are made with a slit diameter of 44 mm, a hole diameter of 10 mm, disc diameter of 140 mm, a disc width of 1.5 mm, a disc gap of 35 mm, a disc gap width of 4 mm, and a shaft length of 50 mm. The results of this study were in the form of torque and pressure drop values. In the variation of engine speed, the highest torque was at 1800 rpm with a torque value of 0.422 Nm, and the highest pressure drop was at 1800 rpm with a pressure drop value of 79161.5 Pa. In the disk gap variation, the highest torque is at a 7 mm disk gap with a torque value of 0.54 Nm and the highest pressure drop is at a 4 mm disk gap with a pressure drop value of 79161.5 Pa. In the variation of disk diameter, the highest torque was found on the disk with a diameter of 180 mm and a torque value of 0.831 Nm, and the highest pressure drop was on a disk with a diameter of 180 mm and a pressure drop value of 86753.5 Pa. In the variation of the number of disks, the highest torque was found at eight disks with a torque value of 0.765 Nm, and the highest pressure drop was found at eight disks with a pressure drop value of 82031.3 Pa. After performing this simulation, it can be concluded that at variations in engine speed, the higher the engine speed, the higher the value obtained and the variations in the disk gap, disk diameter, and number of disks. There are several values of torque that increase and decrease because the input value given cannot always increase the torque value in these variations.
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Zhou, Wan Lin, Wen Hao Chen, and Fu Jun Zhang. "Forming Process Simulation and Optimization of Nickel-Base Superalloy Turbine Disk." Advanced Materials Research 1004-1005 (August 2014): 1156–61. http://dx.doi.org/10.4028/www.scientific.net/amr.1004-1005.1156.

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Turbine disc is the key component of aviation engine, its performance is important to ensure the reliability and safety of the whole aviation engine. In this paper, forging forming of GH4169 alloy turbine disks of certain type aero-engine are discsimulated by DEFORM-3D soft system,these forming methods include next three kinds: common hot die forging, isothermal forging and composite sheath hot die forging.The influences of various forging ways on turbine disk forging quality and the used die are analyzed in order to find the most suitable way of forging. The forging defects in the forging process are analyzed . For basically eliminating these defects, the forging process of superalloy turbine disk are optimized based on the most economical and simple principles and some useful methds are gained，which will provide a reference to actual superalloy turbine disk forging process.
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Traum, Matthew J., and Hope L. Weiss. "Tiny Tesla Turbine Analytical Performance Validation Via Dynamic Dynamometry." E3S Web of Conferences 113 (2019): 03024. http://dx.doi.org/10.1051/e3sconf/201911303024.

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Tesla turbines produce power at high rotation rate and low torque relative to other prime movers. At a tiny scale, this attribute renders Tesla turbines poorly matched to dynamometers designed to characterize electricand gasoline-powered radio-controlled vehicles and kit cars. Techniques are needed to enable Tesla turbine design and performance evaluation. An analytical modelling approach was recently developed by Carey, and a complimentary experimental technique, dynamic dynamometry, can determine Tesla turbine power curves without a dynamometer. This paper mutually validates these approaches by comparing them to each other using results from a 3D printed 4-disk tiny Tesla turbine with characteristic disk inner/outer diameter of 11.54 ± 0.01 mm and 24.85 ± 0.01 mm respectively. The Carey model predicts maximum power output of 0.077 ± 0.015 W, and dynamic dynamometry predicts 0.122 ± 0.008 W, a 36.9% difference. Bounding assumptions were used and more accurate parameter measurements will drive these values closer together. Peculiarities of tiny Tesla turbine operation are also described, including the discovery that turbine spin-down rotational velocity is not linear with time. This phenomenon is likely caused by fluid boundary layer shear between the housing and outer disks. It is not observed in larger Tesla turbines, suggesting a speed, size and/or disk count threshold at which this phenomenon introduces non-trivial parasitic reduction in performance.
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Daniels, W. A., B. V. Johnson, and D. J. Graber. "Aerodynamic and Torque Characteristics of Enclosed Co/Counterrotating Disks." Journal of Turbomachinery 113, no. 1 (January 1, 1991): 67–74. http://dx.doi.org/10.1115/1.2927739.

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Experiments were conducted to determine the aerodynamic and torque characteristics of adjacent rotating disks enclosed in a shroud. These experiments were performed to obtain an extended data base for advanced turbine designs such as the counterrotating turbine. Torque measurements were obtained on both disks in the rotating frame of reference for corotating, counterrotating, and one-rotating/one-static disk conditions. The disk models used in the experiments included disks with typical smooth turbine geometry, disks with bolts, disks with bolts and partial bolt covers, and flat disks. A windage diaphragm was installed at midcavity for some experiments. The experiments were conducted with various amounts of coolant throughflow injected into the disk cavity from the disk hub or from the disk o.d. with swirl. The experiments were conducted at disk tangential Reynolds number up to 1.6 × 107 with air as the working fluid. The results of this investigation indicated that the static shroud contributes a significant amount to the total friction within the disk system, the torque on counterrotating disks is essentially independent of coolant flow total rate, flow direction, and tangential Reynolds number over the range of conditions tested, and a static windage diaphragm reduces disk friction in counterrotating disk systems.
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Shlyannikov, V. N. "Critical Zone Approach for Structural Integrity of Power Engineering Components." Applied Mechanics and Materials 750 (April 2015): 89–95. http://dx.doi.org/10.4028/www.scientific.net/amm.750.89.

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This study is concerned with assessing the integrity of cracked steam turbine rotors components which operate under cyclic loading conditions. Damage accumulation and growth have occurred on the inner surface of slot fillet of key and in a disk and blade rivet attachment. Full-size stress-strain state analysis of turbine disk was performed for different stage of lifetime under considering loading conditions. As a result accumulated damage in critical zones of turbine disks depending on time of loading is defined. The tensile tests were performed for determination the main mechanical properties of disk’s material after loading history. The smooth and notched specimens were cut out from critical zones of turbine disk with given operating time. The low-cycle fatigue tests were performed with the harmonic test-cycle. Additional tests were performed on special designed program test-cycle, which equivalent to start-stop cycle of turbine disk. An engineering approach to the prediction of residual lifetime of turbine disks which is sensitive to the loading history at maintenance is proposed. Approximate estimations of carrying capacity are presented for the different stress-strain state of steam turbine disks at the operation.
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Lee, Seungjin, Daehan Kim, and Joong Park. "Harmonisation of Coolant Flow Pattern with Wake of Stator Vane to Improve Sealing Effectiveness Using a Wave-Shaped Rim Seal." Energies 12, no. 6 (March 19, 2019): 1060. http://dx.doi.org/10.3390/en12061060.

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The rim seal of the gas turbine is intended to protect the material of the turbine disk from hot combustion gases. The study of the rim seal structure is important to minimise the coolant flow and maximise the sealing effect. In this paper, a wave-shaped rim seal for stator disks is proposed and its effect is confirmed by numerical analysis. To characterise the flow phenomena near the wave-shaped rim seal, a simplified model of the wave-shaped rim seal (Type 1 model), which excludes the rotor blade and stator vane, is analysed and compared with the conventional rim seal. Then, through analysis of the wave-shaped rim seal geometry (Type 2 model), which includes the rotor blade and stator vane, a reduction in egress and ingress flow was observed owing to the wave-shaped rim seal, and the sealing effectiveness on the stator disk of turbine was increased by up to 3.8%. Implementation of the wave-shape geometry in the radial seal is a novel choice for turbine designers to consider in future for better-performing and more-efficient turbines.
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Wharton, Sonia, and Kathryn Foster. "Deploying Taller Turbines in Complex Terrain: A Hill Flow Study (HilFlowS) Perspective." Energies 15, no. 7 (April 6, 2022): 2672. http://dx.doi.org/10.3390/en15072672.

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Terrain-induced flow acceleration is presented for the summertime, peak power season at Lawrence Livermore National Laboratory’s Site 300 for the Hill Flow Study (HilFlowS). HilFlowS, designed as an adjunct field campaign to the Department of Energy’s Second Wind Forecasting Improvement Project (WFIP2), provides wind profile observations at a second location in complex terrain for validating numerical atmospheric model simulations and for better understanding flow behavior over hills for wind power generation. One unique feature of HilFlowS was the inclusion of an undergraduate university student who helped plan and execute the experiment as well as analyze wind data from two remote sensing laser detection and ranging (lidar) instruments deployed along parallel ridgelines. HilFlowS examines the trend of building higher into the atmosphere for the purpose of increasing wind turbine power production and evaluates the wind resource in the Altamont Pass Region of Northern California for a set of wind turbines of differing hub-heights and rotor-disk diameters found in the area. The wind profiles show strongly channeled onshore flow above both hills, enhanced by strong subsidence aloft, which produces a wind maximum (Umax) around z = 10 m and strong negative shear throughout all of the evaluated rotor-disks for much of the summer wind season. Under these conditions, shear becomes more negative with increasing hub-height and increasing rotor-disk size. Rotor-disk equivalent wind speed (Uequiv), a measure of the average wind speed across the entire rotor-disk, is compared to hub-height, rotor length, and rated capacity factor for the set of turbines. Uequiv is most closely related to turbine hub-height and is negatively correlated given the low altitude of Umax. Based on these results, building the largest capacity, large rotor-disk wind turbine at the lowest possible hub-height appears to provide turbines in the Altamont with a fast, near-surface, onshore wind resource during the peak power season.
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Yuan, Zhen Wei, Jun Zhang, and Dong Shuai Zhu. "Spanwise Penetration Depth with Turbine Disk Inclination." Advanced Materials Research 945-949 (June 2014): 887–91. http://dx.doi.org/10.4028/www.scientific.net/amr.945-949.887.

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Spanwise penetration depth as a new correlating parameter was introduced in the cascade profile loss correlation of a new loss breakdown scheme for turbine cascade reported in the literature. For the case of an inclined turbine disk, when a turbine disk is inclined to its design position, the blade incidence or inlet flow angle varies with the position of blade on the turbine disk circumference, leading to the variation of spanwise penetration depth. To examine the influences of turbine disk inclination on the spanwise penetration depth, new correlations were developed and numerical simulations were performed with MATLAB. The role that turbine disk inclination plays in the spanwise penetration depth is manifested in a modified inlet flow angle expression on account of turbine disk inclination. It is concluded that the turbine disk inclination has considerable influences on the spanwise penetration depth in the turbine cascade passage.
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Hu, Bo, Xuesong Li, Yanxia Fu, Chunwei Gu, Xiaodong Ren, and Jiaxing Lu. "Axial Thrust, Disk Frictional Losses, and Heat Transfer in a Gas Turbine Disk Cavity." Energies 12, no. 15 (July 29, 2019): 2917. http://dx.doi.org/10.3390/en12152917.

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The gas turbine is a kind of high-power and high-performance energy machine. Currently, it is a hot issue to improve the efficiency of the gas turbines by reducing the amount of secondary air used in the disk cavity. The precondition is to understand the effects of the through-flow rate on the axial thrust, the disk frictional losses, and the characteristics of heat transfer under various experimental conditions. In this paper, experiments are conducted to analyze the characteristics of flow and heat transfer. To ensure the safe operation of the gas turbine, the pressure distribution and the axial thrust are measured for various experimental conditions. The axial thrust coefficient is found to decrease as the rotational speed and the through-flow rate increases. By torque measurements, the amounts of the moment coefficient drop as the rotational speed increases while increase with through-flow rate. In order to better analyze the temperature field within the cavity, both the local and the average Nusselt number are investigated with the help of thermochromic liquid crystal technique. Four correlations for the local Nusselt number are determined according to the amounts of a through-flow coefficient. The results in this study can help the designers to better design the secondary air system in a gas turbine.
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Dissertations / Theses on the topic "Turbine disk"

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Hunter, William. "Actuator disk methods for tidal turbine arrays." Thesis, University of Oxford, 2015. https://ora.ox.ac.uk/objects/uuid:bf8e95df-9e67-4c89-8d9d-1a608a8be0f4.

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Tidal stream energy presents challenges that will require the development of new engineering tools if designs are to harness this energy source effectively. At first glance one might imagine that tidal stream energy can be treated as wind with appropriate adjustment for fluid properties of water over air, and account taken of the harsher offshore environment; both waves and turbulence. However, it is now well accepted that the flow past turbines that are constrained by the local sea bed, sea surface, and possibly also neighbouring turbines and channel sides, will differ markedly from that of an ostensibly unblocked wind turbine. Garrett & Cummins (2007) were the first to demonstrate that operating a turbine in a non- negligibly blocked flow passage presents a different flow solution and importantly a significant opportunity to enhance the power that can be delivered by blocked turbines with the limit of power extraction exceeding the Lanchester-Betz limit for operation of unblocked wind turbines. Although it is impractical to array real turbines across the entire width of a channel it has been proposed to use short arrays of turbines making use of local constructive interference (blockage) effects; Nishino & Willden (2012) showed that although the phenomenal power limits of Garrett & Cummins are unobtainable in a real flow, a significant uplift in the limit of power extraction can be achieved for short fences of turbines arrayed normally to the flow in wide cross-section channels. However, it does not follow that rotors designed using unblocked wind turbine tools are capable of extracting any more power than they are designed for and hence the power uplift made available through blockage effects may be squandered. This thesis sets out to develop design tools to assist in the design of rotors in blocked environments that are designed to make use of the flow confinement effects and yield rotors capable of extracting some of the additional power on offer in blocked flow conditions. It is the pressure recovery condition used in wind turbine design that requires relaxation in blocked flow conditions and hence it is necessary to resort to a computational framework in which the free stream pressure drop can be properly accounted for. The tool of choice is a computational fluid dynamics embedded blade element method. As with all models with semi-empirical content it is necessary to select and test correction models that account for various simplifications inherent to the use of the blade element method over a fully blade resolved simulation. The thesis presents a rigorous comparison of the computational model with experimental data with the various correction methods employed. The tool is then used to design rotors, first for unblocked operation, with favourable comparison drawn to lifting line derived optimal Betz rotor solutions. The final objective of the study is to design rotors for operation in short fence configurations of four turbines arrayed normally to the flow. This is accomplished and it is shown that by using bespoke in situ rotor design it is possible to extract more power than possible with non-blockage designs. For the defined array layout and operating conditions, the bespoke rotor array design yields a power coefficient 26% greater than the implied Betz limit for an unblocked rotor and 4% greater than operating a rotor designed in isolation in the same array.
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Maidana, Cristiano Frandalozo. "Desenvolvimento de turbinas de múltiplos discos : estudo de modelos analíticos e análise experimental." reponame:Biblioteca Digital de Teses e Dissertações da UFRGS, 2015. http://hdl.handle.net/10183/127907.

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Neste trabalho é realizada a concepção, projeto, construção e ensaio de turbinas de múltiplos discos para a verificação dos principais parâmetros e metodologias utilizadas para o projeto e análise do equipamento, além de estudar formas de otimização do equipamento. Assim, uma turbina de múltiplos discos é construída e testada com diferentes configurações de rotores, em uma bancada experimental construída e dimensionada especialmente para esse fim, além da implementação dos métodos analíticos pesquisados no software Engineering Equation Solver (EES). Assim, uma comparação entre os resultados experimentais obtidos por Rice e os modelos de analíticos disponíveis, mostra que o modelo do fator de atrito (FA) é o que melhor representa a operação do equipamento, além de ser o mais versátil dos métodos testados, permitindo que a turbina seja dimensionada e otimizada para várias configurações de construção. Já os resultados experimentais obtidos com um dos protótipos de turbina construído e operado com ar comprimido, mostram que, com modificações simples da geometria, configuração e acabamento superficial dos discos que compõem o rotor, é possível aumentar a eficiência isentrópica em até 35% em relação a turbina padrão montada com a configuração padrão de rotor (discos lisos), sem acarretar prejuízo em alguns dos principais benefícios da utilização deste tipo de equipamento. Os resultados experimentais obtidos mostram também que a eficiência diminui significativamente com o aumento da folga entre o raio externo do rotor e a parte interna da carcaça.
This work is performed conception, design, construction and testing of multiple-disks turbines (MDTs) for the verification of key parameters and methodologies used for the design and analysis of machine as well as consider ways to equipment optimization. Thus, a multiple-disk turbine is constructed and tested with different impeller configurations, in a test rig especially constructed and dimensioned for this purpose, besides the implementation of the analytical methods in software Engineering Equation Solver (ESS). Thus, a comparison between the experimental results obtained by Rice and analytical models available, shows that the friction factor model (FF) is what best represents the operation of the equipment, and is the most versatile of the tested methods, allowing the turbine is sized and optimized for various building configurations. Since the experimental results obtained with one of the turbine prototypes built and operated with compressed air, show that with simple modifications of geometry, configuration and surface finish of the disks that make up the rotor, it is possible to increase the isentropic efficiency by up to 35% compared the standard turbine rotor mounted with the default configuration (flat disks), without causing damage in some of the major benefits of using this type of equipment. The experimental results also show that efficiency decreases significantly with increasing clearance between the outer radius of the rotor and the internal part of the housing.
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Romanoski, Glenn Roy. "The fatigue behavior of small cracks in aircraft turbine disk alloys." Thesis, Massachusetts Institute of Technology, 1990. http://hdl.handle.net/1721.1/32577.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Materials Science and Engineering, 1990.
Includes bibliographical references (leaves 245-258).
by Glenn R. Romanoski, Jr.
Ph.D.
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Khoramzad, Elham. "Fretting fatigue life analysis for a gas turbine compressor blade-disk material combination." Thesis, KTH, Hållfasthetslära, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-284357.

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In order to analyse fretting fatigue life of dove-tail joints used in the compressor stage of a gas turbine, experimental study of different material combinations was conducted using rectangular fatigue specimen and bridge type pads. Specimen and pad interaction was simulated numerically and obtained results was used as input for 2 different crack propagation life prediction methods. The combined effect of stress and fretting damage which was characterised by means of Ruiz parameter was used in order to estimate the crack initiation and finally numerical results were compared to experimental fretting fatigue life. The aim of this thesis was to study the contact fatigue behaviour of titanium alloy (Ti-6Al-4V) in combination with steel alloy (22NiCrMoV12-7).
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Oo, Htet Htet Nwe. "Actuator Disk Theory for Compressible Flow." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1727.

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Because compressibility effects arise in real applications of propellers and turbines, the Actuator Disk Theory or Froude’s Momentum Theory was established for compressible, subsonic flow using the three laws of conservation and isentropic thermodynamics. The compressible Actuator Disk Theory was established for the unducted (bare) and ducted cases in which the disk was treated as the only assembly within the flow stream in the bare case and enclosed by a duct having a constant cross-sectional area equal to the disk area in the ducted case. The primary motivation of the current thesis was to predict the ideal performance of a small ram-air turbine (microRAT), operating at high subsonic Mach numbers, that would power an autonomous Boundary Layer Data System during test flights. The compressible-flow governing equations were applied to a propeller and a turbine for both the bare and ducted cases. The solutions to the resulting system of coupled, non-linear, algebraic equations were obtained using an iterative approach. The results showed that the power extraction efficiency and the total drag coefficient of the bare turbine are slightly higher for compressible flow than for incompressible flow. As the free-stream Mach increases, the Betz limit of the compressible bare turbine slightly increases from the incompressible value of 0.593 and occurs at a velocity ratio between the far downstream and the free-stream that is lower than the incompressible value of 0.333. From incompressible to a free-stream Mach number of 0.8, the Betz limit increases by 0.021 while its corresponding velocity ratio decreases by 0.036. The Betz limit and its corresponding velocity ratio for the ducted turbine are not affected by the free-stream Mach and are the same for both incompressible and compressible flow. The total drag coefficient of the ducted turbine is also the same regardless of the free-stream Mach number and the compressibility of the flow; but, the individual contributions of the turbine drag and the lip thrust to the total drag differs between compressible and incompressible flow and between varying free-stream Mach numbers. It was concluded that overall compressibility has little influence on the ideal performance of an actuator disk.
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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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Akagi, Raymond. "Ram Air-Turbine of Minimum Drag." DigitalCommons@CalPoly, 2021. https://digitalcommons.calpoly.edu/theses/2261.

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The primary motivation for this work was to predict the conditions that would yield minimum drag for a small Ram-Air Turbine used to provide a specified power requirement for a small flight test instrument called the Boundary Layer Data System. Actuator Disk Theory was used to provide an analytical model for this work. Classic Actuator Disk Theory (CADT) or Froude’s Momentum Theory was initially established for quasi-one-dimensional flows and inviscid fluids to predict the power output, drag, and efficiency of energy-extracting devices as a function of wake and freestream velocities using the laws of Conservations of Mass, Momentum, and Energy. Because swirl and losses due to the effects of viscosity have real and significant impacts on existing turbines, there is a strong motivation to develop models which can provide generalized results about the performance of an energy-extractor, such as a turbine, with the inclusion of these effects. A model with swirl and a model with losses due to the effects of viscosity were incorporated into CADT which yielded equations that predicted the performance of an energy-extractor for both un-ducted and ducted cases. In both of these models, for this application, additional performance parameters were analyzed including the drag, drag coefficient, power output, power coefficient, force coefficient, and relative efficiency. For the un-ducted CADT, it is well known that the wake-to-freestream velocity ratio of 1/3 will give the maximum power extraction efficiency of 59.3%; this result is called the Betz limit. However, the present analysis shows that reduced drag for a desired power extraction will occur for wake-to-freestream velocity ratios higher than the value of 1/3 which results in maximum power extraction efficiency. This in turn means that a turbine with a larger area than the smallest possible turbine for a specified power extraction will actually experience a lower drag. The model with the inclusion of swirl made use of the Moment of Momentum Theorem applied to a single-rotor actuator disk with no stators, in addition to the laws of Conservation of Mass, Momentum, and Energy from the CADT. The results from the model w/swirl showed that drag remains unchanged while power extracted decreases with the addition of swirl, with swirl effects becoming more severe for tip speed ratios below about 5. As for CADT, reduced drag for a specified power extraction can be achieved when the wake-to-freestream velocity ratio is higher that than which provides maximum power extraction efficiency. The model w/losses due to viscosity incorporated the losses into the Conservation of Energy relationship. The results from the model w/losses showed that there is a distinct wake-to-freestream velocity ratio at which minimum drag for a specified power output is achieved, and that this velocity ratio is usually—but not always—higher than that for which the power extraction efficiency is a maximum. It was concluded that a lower drag for a specified power output of an energy-extractor can usually be achieved at a wake-to-freestream velocity ratio higher than that which produces the v maximum power extraction efficiency. The latter condition, known as the Betz limit for CADT, and which defines the minimum size for a turbine to provide a specified power extraction, is therefore not the correct target design condition to achieve lowest drag for a small Ram-Air Turbine to power BLDS.
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Foran, Derek. "Experimental and Numerical Modeling of a Tidal Energy Channeling Structure." Thesis, Université d'Ottawa / University of Ottawa, 2015. http://hdl.handle.net/10393/32387.

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Tidal power, or the use of tides for electricity production, exists in many forms including tidal barrages, which exploit tidal head differentials, and turbines placed directly in regions with large tidal current velocities. The latter is actively being investigated in many countries around the world as a means of providing renewable and wholly predictable electricity (cf. wind, solar and wave power). The expansion of the in-stream tidal industry is hindered however by several factors including: turbine durability, deployment and maintenance costs, and the lack of abundant locations which meet the necessary current velocities for turbine start-up and economic power production. A new novel type of augmentation device, entitled the ‘Tidal Acceleration Structure’ or TAS (Canadian patent pending 2644792), has been proposed as a solution to the limited number of coastal regions which exhibit fast tidal currents. In preliminary investigations, the TAS, a simple Venturi section consisting of walls extending from the seafloor to above the high water mark in an hourglass shape, was found as able to more than double current velocities entering the device. The results indicated a significant advantage over other current channeling technologies and thus the need for more in-depth investigations. The main objective of the present study was to optimise the design of the TAS and to predict the power that a turbine placed within it could extract from flow. To do this, two principal methods were employed. Firstly, a 1:50 scale model of the TAS was tested and its shape optimised in a 1.5 m wide flume. Secondly, a 3D numerical model (ANSYS Fluent) was used for comparison with the experimental results. During the tests, a TAS configuration was found that could accelerate upstream velocities by a factor of 2.12. In separate tests, turbines were simulated using Actuator Disc Theory and porous plates. The TAS-plate combination was found to be able to extract up to 4.2 times more power from flow than the stand-alone plate, demonstrating that the TAS could provide turbines with a significant advantage in slower currents. Though further research is needed, including the testing of a larger TAS model in conjunction with a small in-stream turbine, the results of this thesis clearly demonstrate the potential of the TAS concept to unlock vast new areas for tidal energy development.
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Lošák, Petr. "Optimalizace modálního tlumení lopatek vysokotlakých stupňů parních turbín." Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2011. http://www.nusl.cz/ntk/nusl-233951.

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Steam turbine rotor is a very complicated assembly, typically consists of several rotor rows. Due to design limitations and increasing demands on the efficiency of the steam turbines, it is practically impossible to avoid all of the resonant states. The significant vibrations can occur, for example, due to passing resonance state during turbine start up or run out. In the worst case the turbine operates state is close to the resonance state of the rotor row. This leads to the significant oscillation of the bladed disk, and may results in the blade (or blade to disk joints) high cycle fatigue. These parts are highly loaded components and any cracks are unacceptable. Therefore it is absolutely necessary to damp vibration by using, for example, passive damping elements. The damping element analyzed in this thesis is a strap with an isosceles trapezoidal cross section, which is placed in the circumferential dovetail groove in the blade segmental shrouding. The sliding between the contact surfaces leads to the dissipation of energy which causes decreasing of undesirable vibrations. The main aim is to design the optimal dimensions of the strap cross-section with a view to the most effective damping of vibration for a particular turbine operating state. Considered bladed disk has 54 blades which are coupled in 18 packets by segmental shrouding. The damping element is paced in circumferential dovetail groove created in the shrouding. This type of damping element is suitable especially for damping vibrations in the axial direction and only with the mode shape with the nodal diameters. The modal properties of the bladed disk are influenced by the sliding distance. Since the friction force depends on centrifugal force acting on the damping element and on the angle of the side walls of the strap and groove, the sliding distance can be influenced by the damping element dimensions. During the optimization process the best possible size of middle width, height and angle of damping element cross-section is searched. The strap weight, contact area size and flexural stiffness of damping element can be influenced by these parameters. Their change has also impact on the size of the contact pressure and thus on the size of relative motion as well. As stated previously, the damping efficiency is influenced by the relative motion between the damping element and shrouding. Numerical simulation in time domain is very time-consuming, especially for systems containing nonlinearities. In order to verify dynamic behavior of the computational model with the passive friction element in numerical simulations, the simplified model is created. The model is created in the ANSYS environment. The main requirement imposed on this model is to have as small number of degrees of freedom as possible, so the time needed to perform the simulation is reduced to a minimum. To satisfy this requirement the simplified model is a cantilever beam with rectangular cross section. The dovetail groove is created in this model in longitudinal direction. In this groove is damping element. In addition to damping element dimensions optimization, the influence of each design variable on model dynamic behavior is studied. The results are verified experimentally. Experiment also shows other interesting results that confirm the damping element influence on the modal characteristics. The gained knowledge is used to optimize the dimensions of the damping element in the model of the bladed disk.
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Pishva, S. M. R. (S Mohammed Reza) Carleton University Dissertation Engineering Mechanical. "Rejuvenation of gas turbine discs." Ottawa, 1988.

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Books on the topic "Turbine disk"

1

Dunphy, J. R. Development of a fiber optic sensor for turbine disk diagnostics. New York: AIAA, 1985.

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Drexler, Jan. Estimating the DT life of turbine disks using crack state curve approach. Praha, Czechoslovakia: Information Centre for Aeronautics, 1987.

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Wallace, William. Methods for crack growth testing in gas turbine engine disc materials. Ottawa: National Aeronautical Establishment, 1987.

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Delhelay, Davinder Singh. Nonlinear finite element analysis of the coupled thermomechanical behaviour of turbine disc assemblies. Ottawa: National Library of Canada, 1999.

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Olagunju, M. O. A study of efficient recovery of liquid from fine air-liquid mists of the form generated in gas turbine bearing chambers using a rotating porous disc. London: University of East London, 1998.

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V, Zaretsky Erwin, August Richard, and NASA Glenn Research Center, eds. Probabilistic analysis of aircraft gas turbine disk life and reliability. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

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National Aeronautics and Space Administration (NASA) Staff. Experimental Investigation of Turbine Disk Cavity Aerodynamics and Heat Transfer. Independently Published, 2018.

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National Aeronautics and Space Administration (NASA) Staff. Probabilistic Analysis of Aircraft Gas Turbine Disk Life and Reliability. Independently Published, 2018.

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National Aeronautics and Space Administration (NASA) Staff. Fatigue Characterization of Alloy 10: A 1300f Disk Alloy for Small Gas Turbine Engines. Independently Published, 2018.

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Numerical analysis of intra-cavity and power-stream flow interaction in multiple gas-turbine disk-cavities. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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Book chapters on the topic "Turbine disk"

1

Carter, Jace A., Michael Thomas, Tarun Goswami, and Ted Fecke. "Probabalistic Risk Assessment of a Turbine Disk." In Fatigue of Materials II, 71–86. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-48105-0_6.

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Carter, Jace A., Michael Thomas, Tarun Goswami, and Ted Fecke. "Probabalistic Risk Assessment of a Turbine Disk." In Fatigue of Materials II, 71–86. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2012. http://dx.doi.org/10.1002/9781118533383.ch6.

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Qilin, Hong. "The Crack Propagation and Life Estimation of Turbine Disk." In Computational Mechanics ’86, 1361–69. Tokyo: Springer Japan, 1986. http://dx.doi.org/10.1007/978-4-431-68042-0_199.

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Kromine, A. K., P. A. Fomitchov, S. Krishnaswamy, and J. D. Achenbach. "Scanning Laser Source Technique and its Application to Turbine Disk Inspection." In Review of Progress in Quantitative Nondestructive Evaluation, 381–86. Boston, MA: Springer US, 1999. http://dx.doi.org/10.1007/978-1-4615-4791-4_47.

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Gu, Yue Feng, C. Cui, D. Ping, Hiroshi Harada, Akihiro Sato, and J. Fujioka. "Development of New Generation Turbine Disk Superalloys in the HTM21 Project." In Materials Science Forum, 1277–80. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-432-4.1277.

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Kim, J. W. "Stress Analysis of the Turbine Rotor Disk by the Axisymmetric Boundary Element Method." In Boundary Elements XIII, 717–28. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3696-9_57.

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Kanno, Naoya, Masaya Higashi, Ryosuke Takai, Shigehiro Ishikawa, Kota Sasaki, Kenji Sugiyama, and Yoshinori Sumi. "Development and Application of New Cast and Wrought Ni-Base Superalloy M647 for Turbine Disk." In Superalloys 2020, 82–90. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-51834-9_8.

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Gu, Y., Z. Zhong, Y. Yuan, T. Osadal, C. Cui, T. Yokokawa, and H. Harada. "An Advanced Cast-and-Wrought Superalloy (TMW-4M3) for Turbine Disk Applications Beyond 700°C." In Superalloys 2012, 903–10. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2012. http://dx.doi.org/10.1002/9781118516430.ch99.

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Wang, Yanju, Jiaying Jiang, Yong Zhang, Yongjun Guan, and Xingwu Li. "Gradient Speed Control Method to Reduce the Residual Stress on a Turbine Disk in Forging Process." In Lecture Notes in Mechanical Engineering, 1229–35. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-0107-0_116.

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Dahal, Jinesh, Kimberly Maciejewski, and Hamouda Ghonem. "Grain Boundary Deformation and Fracture Mechanisms in Dwell Fatigue Crack Growth in Turbine Disk Superalloy ME3." In Superalloys 2012, 149–58. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2012. http://dx.doi.org/10.1002/9781118516430.ch17.

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Conference papers on the topic "Turbine disk"

1

Kasina, Lakshman, Raghavan Kotur, and Govindaraji Gnanasundaram. "Minimum Weight Design of Aero Engine Turbine Disks." In ASME 2015 Gas Turbine India Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gtindia2015-1250.

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The aero engine rotating parts are always fracture critical components and their failure in service affects the aircraft safety. Rotors / disks will burst at a certain speed if they operate at ever-increasing speed. Rotor burst is one of important failure mode in aero engine and resulting in disk disintegration into multiple fragments with high speed resulting in containment breach. Disks are subjected to fatigue loading and it limits the service life. Fatigue loading on disk includes high temperature environment, tremendous centrifugal and aerodynamic forces caused by blades. The main aspect of turbine disk design is to safe guard against LCF failure. Design of disk should ensure that stresses due to thermal, centrifugal and aerodynamics loads during operating conditions should be within the limits. Turbine disks are also designed to operate at speed above 20% of maximum operating speed for maximum power and referred as over speed capability or burst margin. This over speed capability may require for the aircraft during emergency conditions. The objective of this study is to design a turbine disk for minimum weight. A numerical investigation is performed to predict stresses and burst margins of turbine disk. A parametric disk model is developed with bore width, bore height, web width and web height parameters. Optimization of turbine disk design is carried out to achieve minimum weight. Sensitivity studies are carried out to understand the geometry parameters influence on the stress and burst margins.
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He, Beichang, Youdong Zhou, Ramesh Gambheera, and Shesh K. Srivatsa. "Turbine Disk Forging Process Optimization." In ASME 1999 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/detc99/dac-8604.

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Abstract This paper addresses one of the important aspects of the turbine disk forging process — the design of die geometry to achieve near-net-shape forging. The problem is formulated as a parametric geometry and high-fidelity analysis based optimization problem. The forging weight is minimized within prescribed processing windows and forging rules including bounds on strain, temperature, strain rate, press capacity, dwell time, sonic coverage, fillet radius, draft angles, etc. A fully automated analysis and optimization system that works in a heterogeneous and networked computing environment is built on the top of three commercial software packages: DEFORM for simulating metal forming process, Unigraphics for defining and manipulating geometry, and iSIGHT for software integration and optimization. The system is applied to the optimization of turbine disks.
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Daniels, W. A., B. V. Johnson, and D. J. Graber. "Aerodynamic and Torque Characteristics of Enclosed Co/Counter Rotating Disks." 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-177.

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Experiments were conducted to determine the aerodynamic and torque characteristics of adjacent rotating disks enclosed in a shroud. These experiments were performed to obtain an extended data base for advanced turbine designs such as the counter-rotating turbine. Torque measurements were obtained on both disks in the rotating frame of reference for co-rotating, counter-rotating and one-rotating/one-static disk conditions. The disk models used in the experiments included disks with typical smooth turbine geometry, disks with bolts, disks with bolts and partial bolt covers and flat disks. A windage diaphragm was installed at mid-cavity for some experiments. The experiments were conducted with various amounts of coolant throughflow injected into the disk cavity from the disk hub or from the disk OD with swirl. The experiments were conducted at disk tangential Reynolds number up to 1.6×107 with air as the working fluid. The results of this investigation indicated that the static shroud contributes a significant amount to the total friction within the disk system, the torque on counter-rotating disks is essentially independent of coolant flow total rate, flow direction and tangential Reynolds number over the range of conditions tested and a static windage diaphragm reduces disk friction in counter-rotating disk systems.
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Jun, Li, Fan Ning, and Zhao Xuecheng. "Combined Static and Dynamic Optimization of a Turbine Disk." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-38992.

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Due to high working temperature and rotating speed, turbine disks are crucial parts in gas turbine engines. The weight of disks is always heavy in order to increase the reliability and structural integrity. So optimization design of disks could bring a significant reduction in engine weight. Focusing on a typical Low Pressure Turbine (LPT) disk, this paper improves its design in both static and dynamic characteristics with ANSYS Workbench platform. Based on a 2D parameterized model, the sensitivity of different structural parameters was investigated quickly. Then the optimization process to minimize the mass was conducted by NLPQL (Non-Linear Programming by Quadratic Lagrangian) method with 3D parameterized model. The equivalent stress of disk was limited in static optimization and resonance frequency was also restricted to a safe level through a Campbell diagram in dynamic optimization. A new design plan was acquired through optimization process, which reduces 13.6% of total weight under static and dynamic criteria.
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Tian, Shuqing, and Yatao Zhu. "Disk Heat Transfer Analysis in a Heated Rotating Cavity With an Axial Throughflow." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69185.

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In the rotating disk cavities of aero-engine compressors, buoyancy-induced flow and heat transfer can occur due to thermal gradients between cooling air and hot surfaces. The simplified rotating cavity with two plane discs, a shaft and a cylindrical rim has been investigated numerically and compared with the available measurements. Two models have been solved using a commercial CFD code, Fluent, with the RNG k-ε turbulence model. The first one is the conventional model with only fluid region solved, a temperature profile with the linear radial gradient imposed at the disk walls, and an isothermal boundary condition imposed at the shroud wall. The second one is the model with thick-walled disks and shroud, an adiabatic boundary condition imposed at the outer walls of the disks, and an isothermal boundary condition imposed at the outer wall of the shroud. The fluid and solid are coupled solved simultaneously. The disk temperatures are computed. In the present work, the numerical results are in reasonable agreement with the measurements. The computed disk temperatures in the second model have approximately linear radial gradients over the first three-quarters of the disks, and in the last quarter of the disks the temperature radial gradients are obviously non-linear. The different disk temperature profiles in these two models do not lead to obviously different disk heat transfers. The heat transfer in the rotating cavity leads to a considerable temperature increase of the cavity core fluid, therefore a corresponding increase of the outlet temperature. These two temperature increases are critical for the cooling design in aero-engines.
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Xin, Jianqiang, and Jianjun Wang. "Investigation of Coriolis Effect on Vibration Characteristics of a Realistic Mistuned Bladed Disk." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45453.

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Mistuning, which refers to inevitable variations in blades properties, will change the vibration of bladed disks dramatically. Bladed disks are exposed to effects of forces caused by bladed disk rotation, such as centrifugal and Coriolis forces. However, there is little research on the vibration behavior of a realistic bladed disk with Coriolis force. An investigation of the speed effect, i.e., the effects of centrifugal and Coriolis forces, on the vibration characteristics of a realistic mistuned bladed disk model is presented in this paper. Finite element method (FEM) is used to obtain the system mass, stiffness and damping matrix. The effects of Coriolis force and centrifugal force on the modal frequency and harmonic response characteristics of tuned bladed disk are investigated first, then the modal localization and response characteristics of mistuned bladed disk are researched. This investigation indicates that: Coriolis force has efficient influences on the modal and response characteristics of a realistic mistuned bladed disk: it can both increase and decrease the localization of the mistuned bladed disk for different situations.
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Goswami, Tarun K. "Hot Section Turbine Disk Lifing Philosophies." In ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-363.

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The life prediction of critical gas turbine engine components is carried out using a bank of laboratory test data which is also verified by a comprehensive program on full scale fatigue tests. These tests include carcass for containment, canopy for foreign body ingestion, disks for bolt hole and dovetail/firtree root cracks and blades for thermal shock and fatigue. The life of the majority of these components is limited by low cycle fatigue which eventually is based on ‘initiation’ concepts and first detection of a crack 0.8 mm deep. Safe life design requires a high confidence of 99.9% probability of crack free components. Using safe life design concepts there is a large number of prematurely retired disks from service which have a high potential of useful life left in them. Damage tolerance or fracture mechanics based lifing concepts attempt to utilize this ‘useful’ life by analyzing the cracks. However, these concepts depend on the accuracy of detecting cracks by Non-Destructive Inspection (NDI) techniques. The probability of detection curves do not follow a fixed statistical distribution to give sufficient confidence level to fix the next inspection interval. Probabilistic and deterministic fracture mechanics based lifing philosophies are overviewed.
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Sintay, Stephen D., and Brent L. Adams. "Microstructure Design for a Turbine Disk." In ASME 2004 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASME, 2004. http://dx.doi.org/10.1115/detc2004-57645.

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Cao, Y., J. Ling, R. Rivir, and C. MacArthur. "A Numerical Analysis of Gas Turbine Disks Incorporating Rotating Heat Pipes." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-1461.

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Abstract Radially rotating heat pipes have been proposed for cooling gas turbine disks working at high temperatures. A disk incorporating the heat pipe would have an enhanced thermal dissipation capacity and a much lower temperature at the disk rim and dovetail surface. In this paper, extensive numerical simulations have been made for heat-pipe-cooled disks. Thermal performances are compared for the disks with and without incorporating the heat pipe at different heating and cooling conditions. The numerical results presented in this paper indicate that radially rotating heat pipes can significantly reduce the maximum and average temperatures at the disk rim and dovetail surface under a high heat flux working condition. In general, the maximum and average temperatures at the disk rim and dovetail surface could be reduced by above 250 and 150 degrees, respectively, compared to those of the disk without the heat pipe. As a result, a disk incorporating radially rotating heat pipes could alleviate temperature-related problems and allow a gas turbine to work at a much higher temperature.
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Bhavnani, S. H., J. M. Khodadadi, J. S. Goodling, and J. Waggott. "An Experimental Study of Fluid Flow in Disk Cavities." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-137.

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Results are presented for an experimental study of fluid flow in models of gas turbine disk cavities. Experiments were performed on 70 cm diameter disks for rotational Reynolds numbers up to 2.29 × 106. Velocity and pressure distributions are presented and compared to previous theoretical and experimental studies for a free disk, and an unshrouded and shrouded plane rotor-stator disk system. Minimum coolant flow rates for the prevention of ingress, determined for the case of a simple axial rim seal, compare well with previously published data.
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Reports on the topic "Turbine disk"

1

Pollock, Tresa M., and Michael J. Mills. MEANS 2: Microstructure- and Micromechanism-Sensitive Property Models for Advanced Turbine Disk and Blade Systems. Fort Belvoir, VA: Defense Technical Information Center, February 2008. http://dx.doi.org/10.21236/ada483775.

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Wilson, Dale A., and John R. Warren. Thermal Mechanical Fatigue Crack Growth. An Application for Fracture Mechanics Analyses of Gas Turbine Engine Disks. Fort Belvoir, VA: Defense Technical Information Center, March 1985. http://dx.doi.org/10.21236/ada162634.

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Cowles, B. A., A. B. Thakker, and G. E. King. Fracture Mechanics of Multiple Crack Initiations. An Application for Fracture Mechanics Analysis of Gas Turbine Engine Disks. Fort Belvoir, VA: Defense Technical Information Center, October 1985. http://dx.doi.org/10.21236/ada162998.

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Hamilton, Nicholas. Wake Character in the Wind Turbine Array: (Dis-)Organization, Spatial and Dynamic Evolution and Low-dimensional Modeling. Portland State University Library, January 2000. http://dx.doi.org/10.15760/etd.3079.

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Task 8.4 - High Temperature Turbine Disk Development. Office of Scientific and Technical Information (OSTI), February 1997. http://dx.doi.org/10.2172/634891.

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