Relevant bibliographies by topics / Turbine casing

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Turbine casing'

Author: Grafiati
Published: 4 June 2025
Last updated: 23 June 2025

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Journal articles on the topic "Turbine casing"

1

Yu, Maoyu, Jianfang Wang, Haijun Xuan, Wangjiao Xiong, Zekan He, and Mingmin Qu. "Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test." Aerospace 11, no. 8 (2024): 629. http://dx.doi.org/10.3390/aerospace11080629.

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This paper addresses the critical issue of turbine blade containment in aircraft engines, crucial for ensuring flight safety. Through a comprehensive approach integrating numerical simulations and experimental validations, the containment capabilities of gas turbine engine casings are thoroughly analyzed. The study investigates the impact dynamics, deformation characteristics, and energy absorption mechanisms during blade detachment events, shedding light on the containment process. Based on the multi-stage nature of gas turbines, two different blade structures were designed for turbine blades. Utilizing finite element simulation and the Johnson–Cook constitutive equation, this study accurately simulated single-blade and dual-blade containment scenarios. The simulation results of the single blade indicate that the process of a gas turbine blade impacting the casing primarily consists of three stages. The second stage, where the tenon root strikes the casing, is identified as the main cause of casing damage. Meanwhile, in the dual-blade simulation, the second blade, influenced by the first blade, directly impacts the casing after fracturing, resulting in greater damage. Then, eight corresponding containment tests were conducted based on the simulation results, validating the accuracy of the simulation parameters. Experimental verification of simulation results further confirms the validity of the proposed containment curves, providing essential insights for optimizing casing design and enhancing the safety and reliability of aircraft engines.
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Lazarevikj, M., and Z. Markov. "Automated hydraulic design procedure for a Francis turbine spiral casing." IOP Conference Series: Earth and Environmental Science 1079, no. 1 (2022): 012009. http://dx.doi.org/10.1088/1755-1315/1079/1/012009.

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Abstract The spiral casing of a Francis turbine distributes the water from the penstock to the stay and guide vanes circumferentially and uniformly, which is important for achieving the required flow conditions at the runner entrance. Moreover, the spiral casing is supposed to provide the required inlet velocity in front of the stay vanes and create minimal hydraulic losses. The dimensions and shape of the spiral casing depend on the hydraulic and energy parameters of the turbine. A calculation methodology for a Francis spiral casing hydraulic design is presented in this paper. The methodology developed is based on the main condition to achieve a uniform water flow rate into the stay vanes system and the wicket gate over the entire perimeter. The free vortex flow theory is implemented in this research, where the design is based on the law of constant velocity moment. The parametric definition of the spiral casing makes the geometries generated for certain input combinations suitable for numerical analysis using commercially available Computational Fluid Dynamics (CFD) software. The calculation procedure can be used for any set of energy and geometry turbine parameters, such as water discharge, angle of streamline departing from the spiral casing, and stay ring diameter and height. The automated approach integrating MATLAB and ANSYS Workbench capabilities is presented as a spiral casing design tool. The product is a design solution proposed on basis of the turbine parameters. The spiral casing geometry generation is followed by a CFD analysis. Considering input parameters of different existing Francis turbines, the spiral casing is redesigned accordingly. One of the obtained spiral casings geometry is numerically tested. The results show that the uniform discharge distribution is achieved. The automation of the design procedure allows further optimization based on chosen input parameters.
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K, Arunesh Muthiah. "Comparative Study of Gravitational Water Vortex Turbine(GWVT) with Fibonaccian and Conical Casing." International Journal for Research in Applied Science and Engineering Technology 13, no. 6 (2025): 1704–11. https://doi.org/10.22214/ijraset.2025.72492.

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A gravitational vortex turbine is an eco-friendly micro hydropower generation turbine that operates in ultra-low heads to provide energy in rural areas. Nowadays, the challenging aspects of conical casing vortex turbines are low efficiency and poor vortex dynamics. This paper focuses on a conceptual idea study that serves as a comparison of the results of a self-developed golden ratio spiral-based casing for an ultra-low head vortex turbine to a conical gravitational turbine using SolidWorks flow simulation. A six-blade rear turbine is used for the overall simulation. The turbine is placed at the outlet of the casing, and the values of force acting on the turbine blades are simulated. The torque at the turbine blade is also determined for the generic conical casing and the Fibonaccian casing, which are compared for the results. The relative pressure contour acting on the blades of the turbine is represented in a pictorial form. The torque is compared at each axis and plotted in a graphical format. The results encourage further development of GWVT, as there is an increase in the overall torque and efficiency.
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Komarudin, Udin, Iftika Philo, Nia Nuraeni, and Nissa Syifa Puspani. "Pipe Stress and Turbine Nozzle Load Analysis for HP Steam Inlet and MP Steam Extraction on Turbine Generator 51G201T Capacity 10MW." International Journal of Engineering & Technology 7, no. 4.33 (2018): 214. http://dx.doi.org/10.14419/ijet.v7i4.33.23562.

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Thermal pipe expansion on the turbine greatly affects the performance of the turbine, mainly produces misalignment in turbines. The stress analysis on the pipe and the load on the nozzle is very important to ensure that the stress that occurs is still safe and the load that occurs on the nozzle is still below the allowable load. Field information is known, Steam type of 51-G-201-T, capacity 10 MW, total weighs 58 tons, weight casing 37 tons, which has been operating since July 1989, has been occur misalignment on turbines. Stress pipe and load analysis of turbine nozzles on the turbine using software (Autopipe V8i Select Series 3 Edition by Bentley). In this perspective, calculation methodologies were developed in order to do quick analysis of the most common configurations, according to the codes ASME B31.1 (Piping Power). The results of the pipe stress analysis showed that the maximum sustained stress ratio occurred at point A39 (0.32), maximum displacement stress ratio at point A39 (0.97) and maximum hoop stress ratio at point A09 (0.44), all values below 1. This shows that the stress is still safe. The result of load analysis on the turbine casing is the direction x = -880 kg, y = 6246.4kg, z = -3697.7kg, smaller than the weight of the 37 tones turbine casing, so misalignment is not caused by shifting the turbine casing.
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Zhong, Wenyuan, Jiaqi Li, Zhongyu Yang, Yinli Feng, and Tao Sun. "A Numerical Study of Complex Impact Loads on Thin-Walled Casing of Aeroengine Considering Turbine Guide Vane Structure1." Journal of Physics: Conference Series 2557, no. 1 (2023): 012025. http://dx.doi.org/10.1088/1742-6596/2557/1/012025.

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Abstract As the main load-bearing component of the aero-engine system, the thin-walled casings have the characteristics of large size, complex structure, thin wall, and large area. In addition to the harsh working environment, it is necessary to study applicable preventive measures to contain high-energy fragments to ensure flight safety. The complex load formed by the axial impact and circumferential torsion exerted by the turbine rotor on the exhaust casing is studied, and the model includes the turbine rotor. By analyzing the deformation and energy dissipation of the exhaust casing in the calculation results, the dynamic response of the power turbine and the exhaust casing in the complex impact load is obtained, and it is verified that the initial speed of the power turbine has no obvious relationship with the dynamic response and energy dissipation of the exhaust casing. At the same time, it is concluded that the axial velocity and aerodynamic force of the power turbine have a strong positive correlation with the complex impact load and dynamic response of the exhaust casing. In the follow-up studies and equivalent experiments, these conclusions can be used as a reference for further experimental design.
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Marzec, Krzysztof. "Low-Pressure Turbine Cooling Systems." Encyclopedia 1, no. 3 (2021): 893–904. http://dx.doi.org/10.3390/encyclopedia1030068.

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Modern low-pressure turbine engines are equipped with casings impingement cooling systems. Those systems (called Active Clearance Control) are composed of an array of air nozzles, which are directed to strike turbine casing to absorb generated heat. As a result, the casing starts to shrink, reducing the radial gap between the sealing and rotating tip of the blade. Cooling air is delivered to the nozzles through distribution channels and collector boxes, which are connected to the main air supply duct. The application of low-pressure turbine cooling systems increases its efficiency and reduces engine fuel consumption.
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Bakic, Gordana, Vera Sijacki-Zeravcic, Milos Djukic, Bratislav Rajicic, and Marko Tasic. "Remaining life assessment of a high pressure turbine casing in creep and low cycle service regime." Thermal Science 18, suppl.1 (2014): 127–38. http://dx.doi.org/10.2298/tsci121219179b.

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Thick walled components such as high pressure (HP) steam turbine casings operating under high parameter conditions are subjected to a complex stress state. As a result of that stress state, some parts of HP turbine casing undergo to the creep fatigue caused by the combination of thermal fatigue resulted from repeated start/stop operation and the creep which occurs during long-term operation at high temperature and high-pressure. It is well known that domestic thermal power plants have been in use over 100000 h which means that significant cost is required not only for maintenance, but often for renewal of equipment. Based on comprehensive investigation, the results of residual life assessment of one high pressure steam turbine casing, which belongs to the older turbine generation, taking into account simultaneous action of thermal fatigue and creep, are presented in this paper. Also, the critical flaw crack size of HP turbine casing is determined because this parameter has a strong influence on casing integrity and residual life. The results of residual life assessment provide not only a basis for further maintenance, but also estimated time for reparation or renewal.
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Matthias, Heinz-Bernd, Josef Prost, and Christian Rossegger. "Investigation of the Flow in Pelton Turbines and the Influence of the Casing." International Journal of Rotating Machinery 3, no. 4 (1997): 239–47. http://dx.doi.org/10.1155/s1023621x97000225.

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At the institute for waterpower and pumps at the University of Technology Vienna we do a lot of research work observing the flow in the casing and the buckets of Pelton turbines. One interest of our research is to find criteria to estimate the influence of the splash water distribution in the casing on the turbine efficiency. Knowing the splash water distribution it is further possible to develop methods to provide visual documentation of the flow in and around the buckets from the beginning to the end of interaction.Our measurements have been done on a single jet Pelton turbine with a runner pitch diameter of 420 mm. Our research shows that the casing has great influence to the operation of a Pelton turbine and so it is very important to include the casing as an important factor in all investigations. Aluminum honeycombs have been successful to bring the splashing water under control and to make good visual documentations of the flow.
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Tanino, Tadakazu, Ryo Yoshihara, and Takeshi Miyaguni. "A Study on a Casing Consisting of Three Flow Deflectors for Performance Improvement of Cross-Flow Wind Turbine." Energies 15, no. 16 (2022): 6093. http://dx.doi.org/10.3390/en15166093.

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We investigated the effective use of cross-flow wind turbines for small-scale wind power generation to increase the output power by using a casing, which is a kind of wind-collecting device, composed of three flow deflector plates having the shape of a circular-arc airfoil. Drag-type vertical-axis wind turbines have an undesirable part of about half of the swept area where the inflow of wind results in low output performance. To solve this problem, we devised a casing consisting of three flow deflector plates, two of which were to block the unwanted inflow of wind and the remaining flow deflector plate having an angle of attack with respect to the wind direction to increase the flow toward the rotor. In this study, output performance experiments using a wind tunnel and numerical fluid analysis were conducted on a cross-flow wind turbine with three flow deflector plates to evaluate the effectiveness of the casing on output performance improvement. As a result, it was confirmed that the casing could improve the output performance of the cross-flow wind turbine by approximately 60% at the maximum performance point and could also maintain the output performance about 50% higher compared to the bare cross-flow wind turbine without the casing within a deviation angle of ±10 degrees, even when the casing direction was inclined against the wind direction due to changes in wind direction.
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Salem, Hayder, Adel Mohammedredha, and Abdullah Alawadhi. "High Power Output Augmented Vertical Axis Wind Turbine." Fluids 8, no. 2 (2023): 70. http://dx.doi.org/10.3390/fluids8020070.

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Nowadays, wind energy is one of the most cost-effective and environmentally friendly energies in high demand due to shortages in fossil fuels and the necessity to reduce global carbon footprint. One of the main goals of wind turbine development is to increase the power output of the turbine either by increasing the turbine blade swept area or increasing the velocity of the wind. In this article, a proprietary augmentation system was introduced to increase the power output of vertical axis wind turbines (VAWT) by increasing the free stream velocity to more than two folds. The system comprises two identical airfoiled casings within which the turbine/turbines are seated. The results showed that the velocity slightly increases when decreasing the gap between the casing. It was also found that changing the angle of attack of the housing has more impact on the augmented airspeed. CFD technique was used to assess the velocity and flow of air around the system.
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Dissertations / Theses on the topic "Turbine casing"

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Tapanlis, Orpheas. "Turbine casing impingement cooling systems." Thesis, University of Oxford, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.711623.

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Chen, Hua. "Steady and unsteady performance of vaneless casing radial-inflow turbines." Thesis, University of Manchester, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.291004.

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Šamalík, Jakub. "Parní turbina." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2011. http://www.nusl.cz/ntk/nusl-229866.

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In this master’s thesis, I made a thermodynamic calculation of a steam turbine under the parameters given. In order to increase the efficiency of the low-pressure turbine section and to reduce axial length of the low-pressure rotor, a radial stage is designed in this section. The master’s thesis also includes a design of the low-pressure section. The thesis is divided into chapters, which contains a calculation of the single sections of the turbine. In the introductory chapters, the single sections of the turbine engineered are theoretically discussed. In the conclusion, assessments of the benefits of the use of radial stage are made.
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Kadhim, Hakim Tarteeb Kadhim. "Effect of non-axisymmetric casing on flow and performance of an axial turbine." Thesis, University of Leicester, 2018. http://hdl.handle.net/2381/42811.

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Advances in computer based optimization techniques can be used to enhance the efficiency of energy conversions processes, such as by reducing the aerodynamic loss in thermal power plant turbomachines. One viable approach for reducing this flow energy loss is by endwall contouring. This thesis implements a design optimization workflow for the casing geometry of a 1.5 stage axial flow turbine, towards mitigating secondary flow losses. In this thesis, a new non-axisymmetric endwall design method for the stator casing is implemented through a novel surface definition that draws from observations of the typical secondary flow pattern over the casing. The new casing design technique focuses on manipulating specific flow structures directly while also influencing the surrounding pressure field. This approach is tested on a three-dimensional axial turbine RANS model built in OpenFOAM Extend 3.2, with k-ω SST turbulence closure. Computer-based optimization of the surface topology is demonstrated towards automating the design process. This is implemented using Automated Process and Optimization Workbench (APOW) software. The designs are optimized using the total pressure loss across the full stage as the target function. The optimization and its sensitivity analysis give confidence that a good predictive ability is obtained by the Kriging surrogate model used in the prototype design process. The casing surface parametrization was shown to produce topologically smooth interfaces with the rest of the passage geometry. This was achieved by using the Beta distribution function to design a smooth casing groove path, which is a first application of the Beta distribution function to the contouring of a turbomachine casing. The flow analysis confirms the positive impact of the optimized casing groove design on the turbine isentropic efficiency compared to a reference diffusion based endwall design and compared to the benchmark axisymmetric design, at design and at off design conditions.
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Trávníček, Tomáš. "Parní turbína pro solární elektrárnu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-231806.

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The aim of the master’s thesis is a design of double casing condensing steam turbine with gearbox, reheat and with power output 110 MW for solar power station. The steam turbine has an axial output to the air cooled condenser. The design of the turbine is developed on the basis of concept of Doosan Skoda Power company. It is the main reason this turbine has the impulse blading. There are heat calculation and calculation of heat balance diagram in the first part of the thesis. The system of regeneration consist of three Low Pressure Feedwater Heaters (L.P. FWH), deaerator, and two High Pressure Feedwater Heaters (H.P. FWH). The next part of the thesis is focused on a flow path section of turbine. There is a selection of profile of turbine blades at this part, too. The basic design and strength calculation are available only for high-speed high pressure (HP) part of turbine, as an assignment of the thesis says. There is heat balance diagram for 75 % of nominal power output at the end of thesis. The drawing of longitudinal section of HP part of turbine is the main appendix of this thesis.
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Van, Poppel Bret P. (Bret Patrick) 1969. "Tip casing heat transfer measurements of a film-cooled turbine stage in a short duration facility." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/82202.

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Choi, Myeonggeun. "Thermal control of gas turbine casings for improved tip clearance." Thesis, University of Oxford, 2015. https://ora.ox.ac.uk/objects/uuid:14a9ce6a-2af6-4187-afe7-8c6f8e113855.

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A thermal tip clearance control system provides a robust and flexible means of manipulating the closure between the casing and the rotating blade tips in a jet engine, reducing undesirable tip leakage flows. This may be achieved using an impingement cooling scheme on the external casing of the engine in conjunction with careful thermal management of internal over-tip seal segment cavity. For a reduction in thrust specific fuel consumption, the mass flow rate of air used for cooling must be minimised, be at as low a pressure as possible and delivered through a light weight structure surrounding the rotating components in the turbine. This thesis first characterises the effectiveness of a range of external impingement cooling arrangements in typical engine casing closure system. The effects of jet-to-jet pitch, number of jets, inline and staggered alignment of jets, arrays of jets on flange, on an engine representative casing geometry are assessed through comparison of the convective heat transfer coefficient distributions in a series of numerical studies. A baseline case is validated experimentally. The validation data allowed the suitability of different turbulence closure models to be assessed using a commercial RANS solver. Importantly for each configuration the thermal contraction of an idealised engine casing is predicted using thermo-mechanical finite element models, at a series of operating conditions representing engine idle to maximum take-off conditions. Cooling is provided by manifolds attached to the outside of the engine. The assembly tolerance of these components leads to variation in the standoff distance between the manifold and the casing. For cooling arrangements with promising performance, the study is extended to characterise the variation in closure with standoff distance. It is shown that where a sparse array of non-interacting jets is used the system can be made tolerant of large build misalignments. The casing geometry itself contributes to the thermal response of the system, and, in an additional study, the effect of casing thickness and circumferential thermal control flanges are investigated. Restriction of the passage of heat into the flanges was seen to be dramatically change their effectiveness and slight necking of the flanges at their root was shown to improve the performance disproportionally. High temperature secondary air flowing past the internal face of the engine casing tends to heat the casing, causing it to grow. Experimental and numerical characterisation of a heat transfer within a typical over-tip segment cavity heat transfer is presented in this thesis for the first time. A simplified modelling strategy is proposed for casing and a means to reduce the casing heat pickup by up to 25 % was identified. The overall validity of the modelling approach used is difficult to validate in the engine environment, however limited data from a test engine temperature survey became available during the course of the research. By modelling this engine tip clearance control system it was shown that good agreement to the temperature distribution in the engine casing could be achieved where full surface external heat transfer coefficient boundary conditions were available.
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Thomas, Gregory Alexander. "The effect of a casing geometry modification on blade tip-gap aero-thermodynamics in a transonic, high-pressure turbine." Thesis, University of Oxford, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.443002.

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Ferguson, Jeremy Lee. "A Moving Load Finite Element-Based Approach To Determining Blade Tip Forces During A Blade-On-Casing Incursion In A Gas Turbine Engine." The Ohio State University, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=osu1204131916.

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Vrána, Jan. "Třírotorový lopatkový stroj pro klimatizační systém." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2012. http://www.nusl.cz/ntk/nusl-230158.

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For air cooling in aircrafts is used an air cycle machine. Recently, there is focusing on incresing efficiency of air cycle and due this are added another rotors. Design of machine with three rotors is performed in this thesis.
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Books on the topic "Turbine casing"

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Kelly, Carney, Gallardo V. C, and NASA Glenn Research Center, eds. A study of fan stage/casing interaction models. National Aeronautics and Space Administration, Glenn Research Center, 2003.

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Zhang, Dinghua, Yunyong Cheng, Ruisong Jiang, and Neng Wan. Turbine Blade Investment Casting Die Technology. Springer Berlin Heidelberg, 2018. http://dx.doi.org/10.1007/978-3-662-54188-3.

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E, Steinthorsson, Rigby David L, and Lewis Research Center, eds. Effects of tip clearance and casing recess on heat transfer and stage efficiency in axial turbines. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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United States. National Aeronautics and Space Administration, ed. Tape casting as an approach to an all-ceramic turbine shroud seal. National Aeronautics and Space Administration, 1985.

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United States. National Aeronautics and Space Administration., ed. Advanced single crystal for SSME turbopumps. National Aeronautics and Space Administration, 1989.

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Wang, Wenhu, Dinghua Zhang, Yunyong Cheng, Ruisong Jiang, and Kun Bu. Turbine Blade Investment Casting Die Technology. Springer, 2017.

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Zhang, Dinghua, Yunyong Cheng, Ruisong Jiang, and Neng Wan. Turbine Blade Investment Casting Die Technology. Springer, 2018.

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Panigrahi, Shashi Kanta, and Niranjan Sarangi. Aero Engine Combustor Casing. Taylor & Francis Group, 2020.

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Sarangi, Niranjan, and Sashi Kanta Panigrahi. Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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Book chapters on the topic "Turbine casing"

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Gonzalo, Oscar, Jose Mari Seara, Eneko Olabarrieta, et al. "Case Study 1.2: Turning of Low Pressure Turbine Casing." In Lecture Notes in Production Engineering. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-45291-3_2.

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Madhan Kumar, P., Paresh Halder, and Abdus Samad. "Combined Casing Groove and Blade Tip Treatment for Wave Energy Harvesting Turbine." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-4745-4_89.

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Drtina, Peter, and Andreas Sebestyen. "Numerical Prediction of Hydraulic Losses in the Spiral Casing of a Francis Turbine." In Hydraulic Machinery and Cavitation. Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-010-9385-9_9.

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Kim, Jae Hoon, Duck Hoi Kim, Kyoung Joo Kim, Woo Sung Sim, Young Shin Lee, and Won Shik Park. "The Study on Failure Behavior and Low Cycle Fatigue Life of Hot Gas Casing for Gas Turbine." In Key Engineering Materials. Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-456-1.499.

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Neidel, A., S. Riesenbeck, E. Cagliyan, G. Jeschke, N. Rennau, and V. Müller. "Metallurgical Investigation of Cold-formed Fillet Pieces Made of Metastable Austenitic Stainless Steel, for the Turbine Exhaust Casing of a Heavy-Duty Gas Turbine Engine." In Schadensfallanalysen metallischer Bauteile 2. Carl Hanser Verlag GmbH & Co. KG, 2021. http://dx.doi.org/10.1007/978-3-446-47053-8_11.

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Choi, Young Jin, Young Shin Lee, Jae Hoon Kim, Won Shik Park, and Hyun Soo Kim. "A Study on the Flow and Thermal Stress Analysis of the Hot Gas Casing of the Gas Turbine." In Fracture and Strength of Solids VI. Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-989-x.169.

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Viswanatha Rao, A. N., V. P. S. Naidu, and Soumendu Jana. "Gas Turbine Engine Fan Blade Flutter Detection Using Casing Vibration Signals by Application of Recurrence Plots and Recurrence Quantification Analysis." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5701-9_31.

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Zhang, Dinghua, Yunyong Cheng, Ruisong Jiang, and Neng Wan. "Introduction." In Turbine Blade Investment Casting Die Technology. Springer Berlin Heidelberg, 2017. http://dx.doi.org/10.1007/978-3-662-54188-3_1.

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Zhang, Dinghua, Wenhu Wang, Kun Bu, and Yunyong Cheng. "Digitized Modeling Technology of Turbine Blade." In Turbine Blade Investment Casting Die Technology. Springer Berlin Heidelberg, 2017. http://dx.doi.org/10.1007/978-3-662-54188-3_2.

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Zhang, Dinghua, Yunyong Cheng, Ruisong Jiang, and Neng Wan. "Cavity Design Method for Investment Casting Die of Turbine Blade." In Turbine Blade Investment Casting Die Technology. Springer Berlin Heidelberg, 2017. http://dx.doi.org/10.1007/978-3-662-54188-3_3.

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Conference papers on the topic "Turbine casing"

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Orberg, Alexei N., and Vladimir B. Soudarev. "Gas Turbine High Temperature Casing Upgrade." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68170.

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Due to enormous material losses in the case of emergency, it is vital to ensure the operation reliability of the natural gas pipeline compressor stations (CS). The risk of breakdown is rather high for gas turbines (GT) with total operation time approaching the design-estimated life and particularly for those in which the actual period of operation exceeds this value. Over 25% of turbine drives working on natural gas transportation net in Russia have exceeded their design life [1]. For instance, around 600 gas turbines of the GTC-10-4 type (10MW power) are still in service despite their 120,000–160,000 hours of operation (more than 1,000 gas turbines GTC-10 type have been made and installed at natural gas pumping stations in the seventies in Russia). These gas turbines contain several critical components. Most of them are related to the high temperature parts, including inner high-temperature turbine casing (ITC). This ITC is a kind of a collector (duct) connecting a combustion chamber outlet and the turbine’s entry. Combined with an insulation layer, it serves as a protective shield for outer (main) turbine casing against the effect of hot gases. Notwithstanding the fact that the GTC-10-4 turbine has a modest inlet gas temperature (TIT∼800°C), there are various problems with the ITC shape and state during the turbine’s operation. The ITC operates under conditions of dramatic temperature changes, pressure drops, extended periods of high temperature. All these factors can cause the ITC shell deformations, which results in poor turbine performances. Regular maintenance inspections including opening a turbine do not permit to establish reasons for dramatic changes in the ITC shape. A detailed numerical analysis has been performed to better understand the ITC dynamics over its service period of operation. Moreover, it should be observed that ITC forms a flow prior to entering a turbine. Then, gas flow is directed to the first stage nozzles of the turbine. Advanced numerical flow investigation methods were applied to improve hot gas distribution in front of the turbine. A considerable decrease in velocity nonuniformity was achieved both radially and circumferentially through the ITC shape optimization. Great need in this component stimulated introduction of a new manufacturing technology aimed at production of new ITCs and replacement of numerous defective ones still used at natural gas pumping stations across Russia. Results of thermo-deformation analysis and numerical flow investigation for various ITC configurations are presented in the paper. It also contains proposals for improving the state of the ITC and outer turbine casing (OTC) in the result of the fixing unit development and applying a new insulation material.
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Anderson, Rodger O. "Gas Turbine Compressor Casing Repair." In ASME 2005 Power Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/pwr2005-50176.

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Many older heavy duty gas turbine models have a very simple compressor casing design for attaching the stationary blades. It consists of grooves machined into a cast iron casing into which are slid blades with square bases. These bases have extending ears on two sides that engage undercut grooves in the main groove. This design works well, however, when the blade groove is very close to an extraction slot this results in a thin ligament in the casing which eventually cracks. This allows blades to liberate into the flow stream which results in major engine damage. One engine, the GE frame 5 with compressor cast iron casings has a tendency to crack in the blade attachment groove at the horizontal joint in row 10 where the air extraction is taken. The casing hook tends to bend due to the aerodynamic forces on the blades. An analysis shows how the blade forces are transferred to the weak casing ligament. This results in a crack at the thin ligament. The bent and cracked casing hooks are generally visible through a borescope inserted into the extraction cavity from the air pipe flanges. If this situation is not repaired, the cracks can lead to both casing material and blade liberation into the compressor flow stream. A quick and low cost repair has been developed to restore these engines to a reliable operating condition.
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Noushad, Jisha, Anand Babu Dhamarla, and Pavan Kumar. "Casing Treatment of Centrifugal Compressors." In ASME 2015 Gas Turbine India Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gtindia2015-1337.

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The operating range of any compressor is controlled by Surge and Choke. Surge occurs at lower mass flow rates with large pressure fluctuations and flow reversals, while choke occurs at higher mass flow rates when the flow rate reaches the limit which compressor can discharge. Ported shroud is a cost effective casing treatment that can greatly improve operating range of centrifugal compressors. By removing the stagnant and reverse flow from shroud wall boundary-layer region and recirculating it to impeller inlet, it has been demonstrated that larger range of operability can be achieved without much loss on compressor efficiency. This paper demonstrates the improvement of a centrifugal compressor operational range with ported shroud configuration. A series of CFD simulations were carried out with open source centrifugal compressor geometry (NASA HPCC 4:1) to create performance characteristics/speed-lines. The CFD methodology and practices were validated by comparing the results with the experimental data. Performance evaluation of ported shroud configuration is done with respect to solid shroud. Ported shroud compressor is proven to give higher choke mass flow and also a better surge margin compared to the Solid shroud model. The phenomena of in-flowing and out-flowing port have also been demonstrated. Emphasis was given to understand how ported shroud helps to achieve a better performance. A design optimization study has also been carried out in order to establish the optimum ported shroud configuration. Design parameter such as port location has been selected and the effect of this parameter on the performance of the compressor is studied using CFD. Optimum port geometry was proposed.
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Eastman, John A. "Casing Distortion Control Using Pseudo Flanges." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-103.

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Axial ribs have been added to gas turbine stationary casings to reduce casing ovalization and allow tighter blade tip clearances to be maintained. Test experience showing blade rub patterns on stator casings due to casing ovalization is presented. Classical solution techniques are presented which demonstrate trends and the relative roundness and attenuation benefits of adding the axial ribs which increase the order of the casing response. The results of finite element studies using 2D solid modeling techniques are compared to the classical solutions. Examples of applications on industrial gas turbine hardware are presented.
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Hu, Yifeng, Puning Jiang, Xingzhu Ye, et al. "Lifetime Assessment of Steam Turbine Casing." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43495.

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Nowadays, in order to accommodate electrical grids that include fluctuating supplies of green energy, more and more fossil power plants are increasingly required to start up and shut down frequently. The increased number of stress cycles leads to a significant reduction of lifetime. In this paper, numerous load cycles of steam turbine casing including various start up and shut down conditions were numerically investigated by using the finite element analysis (FEA). The total strain throughout the cycles was directly calculated by the elastic-plastic material model. The delta equivalent total strain was determined by rainflow count method, and the assessment of lifetime was evaluated.
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Mitchell, Ryan D., Henry L. Bernstein, and Peggy L. Talley. "Casing Distortion of GE Frame 3 Gas Turbines." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38965.

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A study of casing distortion in General Electric MS3002 gas turbines used in the oil and gas industry revealed significant distortion for MS3002 Models C through G. The primary distortion problem was ovalization of the turbine casing, which could occur in either the horizontal or vertical directions. Malfunctioning of the water cooling system, or improper disassembly and assembly procedures can cause casing distortion. The MS3002 Models A-G gas turbines have water cooled turbine casings, and malfunctioning of their cooling water systems, regardless of distortion, is also a significant problem.
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Ellis, Fred V., Ian G. Wright, and Philip J. Maziasz. "Review of Turbine Materials for use in Ultra-Supercritical Steam Cycles." In AM-EPRI 2004, edited by R. Viswanathan, D. Gandy, and K. Coleman. ASM International, 2004. http://dx.doi.org/10.31399/asm.cp.am-epri-2004p0535.

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Abstract A study is being conducted on turbine materials for use in ultra-supercritical (USC) steam power plants, with the objective of ensuring no material-related impediments regarding maximum temperature capabilities and the ability to manufacture turbine components. A review of the state-of-the-art and material needs for bolting and casing applications in USC steam turbines was performed to define and prioritize requirements for the next-generation USC turbines. For bolting, several potentially viable nickel-base superalloys were identified for service at 760°C, with the major issues being final material selection and characterization. Factors limiting inner casing material capabilities include casting size/shape, ability to inspect for discontinuities, stress rupture strength, and weldability for fabrication and repairs. Given the need for precipitation-strengthened nickel-base alloys for the inner casing at 760°C, the material needs are two-fold: selection/fabrication-related and characterization. The paper provides background on turbine components and reviews the findings for bolting and casing materials.
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Mathioudakis, K., E. Loukis, and K. D. Papailiou. "Casing Vibration and Gas Turbine Operating Conditions." 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-78.

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The results from an experimental investigation of the compressor casing vibration of an industrial Gas Turbine are presented. It is demonstrated that statistical properties of acceleration signals can be linked with engine operating conditions. The power content of such signals is dominated by contributions originating from the stages of the compressor, while the contribution of the shaft excitation is secondary. Using non-parametric identification methods, accelerometer outputs are correlated to unsteady pressure measurements taken by fast response transducers at the inner surface of the compressor casing. The transfer functions allow reconstruction of unsteady pressure signal features from the accelerometer readings. A possibility is thus provided, for “seeing” the unsteady pressure field of the rotor blades without actually penetrating through the casing, but by simply observing its external surface vibrations.
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Khalid, Syed. "A Practical Compressor Casing Treatment." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-375.

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A three stage compressor test incorporating casing inserts comprised of compound angled honeycomb cells demonstrated up to 10% higher stall margin than circumferential grooves casing treatment. This is attributed to effective tip flow energization resulting from the unsteady flow induced in and out of the cells as the blade tip sweeps by the cell openings. The rationale for selecting the cell inclination angles both relative to the normal and the tangential directions is discussed. The design intent of the cell orientation is to induce a high cell exit velocity as well as to impart a degree of flow alignment to the injected jets. A first order calculation of cell exit velocity variation based on the cell pressure/volume dynamics is indicative of unsteady blowing which is theorized to effectively mix the tip suction side flow and to enhance the tip flow streamwise momentum. This theory is partially substantiated by the presented compressor test results showing improved radial total pressure profiles, stage characteristics, and stall margin. Since a few unhealthy stages of a multi-stage compressor could make it stall prone, casing treatment of those weak stages could dramatically increase stall margin with negligible impact on overall adiabatic efficiency. In addition to the aerodynamic effectiveness, the mechanical suitability of this casing treatment to multistage compressors, based on its demonstrated abradability and packageability, is discussed.
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Johnston, David. "Solar Turbine with Optical Coupling of Radiation into the Turbine Casing." In 2012 IEEE PES Asia-Pacific Power and Energy Engineering Conference (APPEEC). IEEE, 2012. http://dx.doi.org/10.1109/appeec.2012.6306954.

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Reports on the topic "Turbine casing"

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Jay. L51723 Guidelines for Sound Power Level Measurements Compressor Equipment. Pipeline Research Council International, Inc. (PRCI), 1994. http://dx.doi.org/10.55274/r0010419.

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Increasing legislation and public awareness of noise are intensifying the efforts of industries today to reduce the noise. The natural gas industry has proved that it is one of the industrial leaders in its awareness of noise problems and has maintained a vigorous research program in noise control for over 30 years. A noise survey can be done in several ways: point measurements, grid point methods, contour methods, scanning techniques, etc. The selection of the method depends on the accuracy required, available personnel, expertise etc. For the most accurate determination of sound power, the scanning method using sound intensity measurements is considered to be the best available in present day circumstances. This method is discussed in detail in later chapters. Point and grid point measurements are useful to determine the Sound Pressure Level, but are of limited use in quantifying the Sound Power Level of a noise source in a complex and multi-source environment such as a compressor station. Guidelines for Sound Power Level Measurements for Compressor Station Equipment Report documents the development of guidelines for in-situ sound power level measurements for compressor station equipment, with sample calculations. Measurement of equipment noise levels in a complex, multi-source environment is very difficult and may be accomplished by several methods. These guidelines specify the sound intensity approach that can be used in almost any field situation. The sound power guidelines described in this report specify the sound intensity approach as the primary measurement method since it can be used in almost any field situation to determine the sound power of a source. In open spaces without reflecting surfaces (except the ground plane) sound pressure measurements may give satisfactory estimates of the sound power of noise sources if background noise is low and other sources can be turned off. Inside a compressor building, the modified reverberation room approach may be allowed, but then only the total sound power can be determined unless background sources can be controlled or other sources turned off. Lastly, the standard guidelines developed were used to conduct field measurements of the sound power of four equipment noise sources including: a) turbine casing, b) turbine air inlet, c) cooler and d) exhaust stack.
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Cooperman, Aubryn. Large Castings for Wind Turbines. Office of Scientific and Technical Information (OSTI), 2023. http://dx.doi.org/10.2172/1995803.

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