The Experts below are selected from a list of 1443 Experts worldwide ranked by ideXlab platform
Bharathi V. - One of the best experts on this subject based on the ideXlab platform.
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Advanced Cooling of Gas Turbine Blades with Sodium Liquid and Air
'Infogain Publication', 2017Co-Authors: Jose J., Bharathi V.Abstract:Gas turbines are extensively used for air craft propulsion, land based power generation and industrial applications. Thermal efficiency of gas turbine can be improved by increasing turbine Rotor Inlet Temperature. The current Rotor Inlet Temperature in advanced gas turbine is for above the melting point of blade material. A sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. Gas turbines are cooled externally and internally. Several methods have been suggested for the cooling of blades and vanes. The technique that describes in thesis is by cooling the blade by circulating sodium liquid filled inside it. The hot less denser sodium liquid travels the bottom region of the blade and transfer heat to the high velocity air passing near it. In this thesis a turbine blade model is designed and modeled in CATIA V5. CFD analysis of the model is performed for variant models. A comparative study of the results like Temperature, turbulent kinetic energy and heat transfer rate through cooling air is made to find the best model which delivers effective cooling of the blade
Igor Loboda - One of the best experts on this subject based on the ideXlab platform.
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a comparative analysis of turbine Rotor Inlet Temperature models
Volume 3: Controls Diagnostics and Instrumentation; Education; Electric Power; Microturbines and Small Turbomachinery; Solar Brayton and Rankine Cycle, 2011Co-Authors: Cristhian Maravilla Herrera, Sergiy Yepifanov, Igor LobodaAbstract:Life usage algorithms constitute one of the principal components of gas turbine engines monitoring systems. These algorithms aim to determine the remaining useful life of gas turbines based on Temperature and stress estimation in critical hot part elements. Knowing Temperatures around these elements is therefore very important. This paper deals with blades and disks of a high pressure turbine (HPT). In order to monitor their thermal state, it is necessary to set thermal boundary conditions. The main parameter to determine is the total gas Temperature in relative motion at the Inlet of HPT blades Tw * . We propose to calculate this unmeasured Temperature as a function of measured gas path variables using gas path thermodynamics. Five models with different thermodynamic relations to calculate the Temperature Tw * are proposed and compared. All Temperature models include some unmeasured parameters that are presented as polynomial functions of a measured power setting variable. A nonlinear thermodynamic model is used to calculate the unknown coefficients included in the polynomials and to validate the models considering the influence of engine deterioration and operating conditions. In the validation stage, the polynomial’s inadequacy and the errors caused by the measurement inaccuracy are analyzed. Finally, the gas Temperature models are compared using the criterion of total accuracy and the best model is selected.Copyright © 2011 by ASME
E Romero - One of the best experts on this subject based on the ideXlab platform.
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Rotor blade heat transfer characteristics for high pressure turbine stage under Inlet Temperature and velocity traverses
ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, 2014Co-Authors: A Rahim, E RomeroAbstract:One of the key considerations in high pressure (HP) turbine design is the heat load experienced by Rotor blades. The impact of turbine Inlet non-uniformities on the blades in the form of combined Temperature and velocity traverses, typical for a lean burn combustor exit, has rarely been studied. For general HP turbine aerothermal designs, it is also of interest to understand how the behavior of a lean burn combustor traverses (hot streak and swirl) might contrast with those for rich burn combustion (largely hot streak only).In the present work, a computational study has been carried out on the aerothermal performance of a HP turbine stage under non-uniform Temperature and velocity Inlet profiles. The analyses are primarily conducted for two combined hot streak and swirl Inlets, with opposite swirl directions. In addition, comparisons are made against a hot streak only case and a uniform Inlet. The effects of three NGV shape configurations are investigated; namely, straight, compound lean (CL) and reverse compound lean (RCL).The present results show that there is a qualitative change in the roles played by heat transfer coefficient (HTC) and fluid driving (‘adiabatic wall’) Temperature, Taw. It has been shown that the blade heat load distribution for a uniform Inlet is dominated by HTC, whilst for a hot streak only case it is wholly influenced by Taw. However, in contrast to the hot streak only case, the case with a combined hot streak and swirl shows a role reversal with the HTC being dominant in determining the heat load. Additionally, it is seen that the swirling flow radially redistributes the hot fluid within the NGV passage considerably, leading to a much ‘flatter’ Rotor Inlet Temperature profile compared to its hot streak only counterpart. Further, the Rotor heat transfer characteristics for the cases with the combined traverses are shown to be strongly dependent on the NGV shaping and the Inlet swirl direction, indicating the potential for future design space exploration. The present findings underline the need to clearly define relevant combustor exit Temperature and velocity profiles when designing and optimizing NGVs for HP turbine aerothermal performance.Copyright © 2014 by Rolls-Royce plc
Dr.yogananda A - One of the best experts on this subject based on the ideXlab platform.
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CFD ANALYSIS ON RADIALCOOLING OF GAS TURBINE BLADE
2017Co-Authors: Harsha D A, Dr.yogananda AAbstract:Gas turbines are extensively used for air craft propulsion,land based power generation and industrial applications. Thermal efficiency of gas turbine improved by increasing turbine Rotor Inlet Temperature. The current Rotor in let Temperature in advanced gas turbine is for above the melting point of blade material. A sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. Gas turbines are cooled externally and internally. Several methods have been suggested for the cooling of blades and vanes. The techniques that involve to cool the blades and vanes by using cooling methods is to have radial holes to pass high velocity cooling air along the blade span. In this thesis,a turbine blade is designed and modelled in CATIA v5 and ICEM CFD software. https://www.ijiert.org/paper-details?paper_id=14108
Behera Akhilesh - One of the best experts on this subject based on the ideXlab platform.
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CFD Analysis of Matrix Cooling Method in Gas Turbine Blades
2015Co-Authors: Behera AkhileshAbstract:Gas turbines are extensively in use for aircraft propulsion, land-based power generations, and various industrial applications. Thermal efficiency and the power output of a gas turbine increases with increase in turbine Rotor Inlet Temperature (RIT). The current RIT level in many advanced gas turbines is far above the melting point of the used blade material. Therefore, along with development in high Temperature material, a more sophisticated cooling scheme must be developed for continuing the safe operation of gas turbines with high performances. Gas turbine blades can be cooled internally as well as externally. This paper is focused on the internal cooling of turbine blades and vanes of a gas turbine. Internal cooling can be achieved by passing coolant through various enhanced serpentine passages inside the blade and extracting heat from outside of the blades. Jet impingement, matrix cooling, rib turbulator, dimple and pin fin cooling are utilized as the methods of internal cooling, which are presented in various articles. Due to the different enhancement in heat transfer and in pressure drop, they are being used in specific part of the blades and the vanes on a gas turbine. The matrix cooling, also known as lattice-work or vortex cooling provides a good strength to blades by the layers of ribs which intersect each other from the opposite wall. A significant increase in the heat transfer is obtained due to an increase in heat transfer area, impinging and in swirling flows (which helps to promote turbulence), induced by the geometry of the matrix cooling channels
