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Journal articles on the topic 'Turbine blade cooling'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

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

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Gas turbines are extensively used for aircraft propulsion, land-based power generation, and industrial applications. Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperature (RIT). The current RIT level in advanced gas turbines is far above the .melting point of the blade material. Therefore, along with high temperature material development, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. Gas turbine blades are cooled internally and externally. This paper focuses on externa

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2

Han, Je-Chin. "Recent Studies in Turbine Blade Cooling." International Journal of Rotating Machinery 10, no. 6 (2004): 443–57. http://dx.doi.org/10.1155/s1023621x04000442.

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Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. Developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced gas turbines. Gas turbine blades are cooled internally by passing the coolant through several rib-enhanced serpentine passages to remove heat conducted from the outside surface. External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface in order to form

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3

HARSHA, D. A., and A. DR.YOGANANDA. "CFD ANALYSIS ON RADIALCOOLING OF GAS TURBINE BLADE." IJIERT - International Journal of Innovations in Engineering Research and Technology 4, no. 7 (2017): 47–51. https://doi.org/10.5281/zenodo.1459059.

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<strong>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 co

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4

Xu, Liang, Zineng Sun, Qicheng Ruan, Lei Xi, Jianmin Gao, and Yunlong Li. "Development Trend of Cooling Technology for Turbine Blades at Super-High Temperature of above 2000 K." Energies 16, no. 2 (2023): 668. http://dx.doi.org/10.3390/en16020668.

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Aeroengines and heavy-duty gas turbines are the core power equipment in the field of national defense and energy. Their research and development (R&D) level and manufacturing level represent the status of a country’s heavy industry in the world. The common cooling technologies of turbine blades including impingement cooling, film cooling, effusion cooling, layer cooling, pin fin cooling, and rough ribs were introduced in this paper. With the continuous improvement of the efficiency and performance of aeroengines and gas turbines, the turbine inlet temperature increases gradually every year

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5

Sharma, Chirag, Siddhant Kumar, Aanya Singh, et al. "Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies." International Journal of Heat and Technology 39, no. 2 (2021): 403–16. http://dx.doi.org/10.18280/ijht.390209.

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Developments in the gas turbine technology have caused widespread usage of the Turbomachines for power generation. With increase in the power demand and a drop in the availability of fuel, usage of turbines with higher efficiencies has become imperative. This is only possible with an increase in the turbine inlet temperature (TIT) of the gas. However, the higher limit of TIT is governed by the metallurgical boundary conditions set by the material used to manufacture the turbine blades. Hence, turbine blade cooling helps in drastically controlling the blade temperature of the turbine and allows

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6

Wang, Wen, Yan Yan, Yeqi Zhou, and Jiahuan Cui. "Review of Advanced Effusive Cooling for Gas Turbine Blades." Energies 15, no. 22 (2022): 8568. http://dx.doi.org/10.3390/en15228568.

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Turbine inlet temperature has continuously increased to improve gas turbine performance during the past few decades. Although internal convection cooling and traditional film cooling have contributed significantly to the current achievement, advanced cooling schemes are needed to minimize the coolant consumption and maximize the cooling efficiency for future gas turbines. This paper conducts a comprehensive review of advanced effusive cooling schemes for gas turbine blades. First, the background and the history of turbine blade cooling are introduced. Then, the metrics of effusive cooling effi

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7

Varatharajulu Purgunan, Gokkul Raj, Majid Asli, Teodosio Nacci, Daniela Anna Misul, Simone Salvadori, and Panagiotis Stathopoulos. "Film Cooling Modeling in a Turbine Working under the Unsteady Exhaust Flow of Pulsed Detonation Combustion." Energies 17, no. 6 (2024): 1312. http://dx.doi.org/10.3390/en17061312.

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Pressure gain combustors (PGCs) have demonstrated significant advantages over conventional combustors in gas turbine engines by increasing the thermal efficiency and reducing the pollution emission level. PGCs use shock waves to transfer energy which contributes to the increase in outlet total pressure. One of the major obstacles in the actual implementation of PGCs in the gas turbine cycle is the exploitation of the highly unsteady flow of the combustor outlet with the downstream turbine. Because of the higher outlet temperature from the PGCs, the turbine blade cooling becomes essential. Due

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8

You, Huaqing. "Effect of thermal barrier coating on the thermal characteristic of turbine blade and its geometric optimization." Theoretical and Natural Science 14, no. 1 (2023): 62–77. http://dx.doi.org/10.54254/2753-8818/14/20240880.

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Thermal barrier coatings (TBC) and cooling structures are critical factors influencing the performance of aviation turbine blades. In order to investigate the effects of TBC and different cooling structures on the operating temperature and thermal stress of turbine blades, this study establishes a three-dimensional fluid-thermal-solid coupling model for aviation turbine blades. Based on this model, the study analyzes the effect of TBC thicknesses and different design architectures on the blade thermal characters, including temperature distribution and thermal stress analysis. Stress analysis i

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9

Kumar, S., and O. Singh. "Performance evaluation of a transpiration-cooled gas turbine for different coolants and permissible blade temperatures considering the effect of radiation." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 225, no. 8 (2011): 1156–65. http://dx.doi.org/10.1177/0957650911404305.

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Successful gas turbine technology is based significantly upon the introduction of new blade materials with increased permissible temperature for gas turbine blades and/or the use of efficient means and methods of turbine blade cooling in order to achieve the highest possible turbine inlet temperature. The gas turbine blade cooling models found in literature indicate that the effect of radiation from elevated temperature gases is generally not considered. However, the radiative heat transfer always occurs owing to the presence of mainly carbon dioxide and water vapour in the combustion products

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10

Hao, Ning, and Weilin Yi. "Performance analysis of air-cooled turbine based on source terms method." Journal of Physics: Conference Series 2882, no. 1 (2024): 012036. http://dx.doi.org/10.1088/1742-6596/2882/1/012036.

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Abstract Investigating turbine blade cooling and blade tip clearance leakage is crucial for reducing turbine losses and enhancing overall engine performance. Therefore, this paper uses the E3 two-stage high-pressure turbine as a case and employs the source term method to model the film cooling configuration, validating its efficacy and examining the performance parameters and flow field characteristics of air-cooled turbines under varying blade tip clearances. The outcomes demonstrate that the source term approach accurately forecasts the comprehensive performance parameters of air-cooled turb

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11

Kim, Kwang Su, and Youn Jea Kim. "Experimental Study on the Film Cooling Performance at the Leading Edge of Turbine Blade Using Infrared Thermography." Key Engineering Materials 326-328 (December 2006): 1161–64. http://dx.doi.org/10.4028/www.scientific.net/kem.326-328.1161.

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In order to protect turbine blades from high temperature, film cooling can be applied to gas turbine engine system since it can prevent corrosion and facture of material. To enhance the film cooling performance in the vicinity of the turbine blade leading edge, flow characteristics of the film-cooled turbine blade have been investigated using a cylindrical body model. Mainstream Reynolds number based on the cylinder diameter was 1.01×105 and the mainstream turbulence intensities were about 0.2%. CO2 was used as coolant to simulate the effect of coolant-tomainstream density ratio. The effect of

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12

Zhang, Han, Hua Chen, Chao Ma, and Feng Guo. "INVESTIGATION OF CONJUGATED HEAT TRANSFER FOR A RADIAL TURBINE WITH IMPINGEMENT COOLING." Journal of Physics: Conference Series 2087, no. 1 (2021): 012037. http://dx.doi.org/10.1088/1742-6596/2087/1/012037.

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Abstract Radial turbine is widely used in micro-turbines, turbochargers, small jet engines and expanders, and the pursue of high system efficiency has resulted in elevated turbine inlet temperatures for some of its applications, threatening its reliability. There are, however, few cooling studies on radial turbines. This paper studies the jet impingement cooling of a turbocharger radial turbine. A small amount of air (coolant), which could come from compressor discharge cooled by an intercooler, is injected through a few jet holes on the heat shield of the turbine onto the upper part of turbin

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13

Kumar, Micha, N. Alagumurthi, and K. Palaniradja. "Conjugated heat transfer analysis of gas turbine vanes using MacCormack's technique." Thermal Science 12, no. 3 (2008): 65–73. http://dx.doi.org/10.2298/tsci0803065k.

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It is well known that turbine engine efficiency can be improved by increasing the turbine inlet gas temperature. This causes an increase of heat load to the turbine components. Current inlet temperature level in advanced gas turbine is far above the melting point of the vane material. Therefore, along with high temperature material development, sophisticated cooling scheme must be developed for continuous safe operation of gas turbine with high performance. Gas turbine blades are cooled internally and externally. Internal cooling is achieved by passing the coolant through passages inside the b

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14

Kashyzadeh, Kazem Reza, and Kambiz Souri. "A Short Introduction of Blade Cooling Mechanisms in Old Gas Turbines with the Aim of Proper Distribution of Temperature Profile." Journal of Advanced Thermal Science Research 10 (December 29, 2023): 98–111. http://dx.doi.org/10.15377/2409-5826.2023.10.8.

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Presently, old gas turbines are used in the industry of some developing countries without high tech, which face many problems in the field of thermal efficiency and output power. Typically, turbines operate in the temperature range of 1200 to 1500 degrees Celsius. Many studies have been done to increase the efficiency of such systems. The results show that this increase in temperature at the inlet of the gas turbine has negative consequences, such as increasing the thermal load of the turbine blades and thus reducing the lifetime of the blades. On the other hand, a damaged blade can cause seri

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15

Cao, Bo, Yi Yu, Jingchuan Sun, and Lina Zhang. "Optimization of oil-cooled blade structures based on data-driven approaches." Journal of Physics: Conference Series 2955, no. 1 (2025): 012008. https://doi.org/10.1088/1742-6596/2955/1/012008.

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Abstract The continuous escalation of turbine inlet temperatures in aero-engine applications has rendered traditional air-cooling techniques insufficient to undertake the efficient cooling of turbine guide vanes solely. In this context, oil-cooling technology has emerged as a potent complement to air-cooling methods. The stable operating temperature limit of fuel, when used as a coolant, is merely 523 K. In contrast, turbine guide vanes operate at temperatures as high as 1, 900 K, with material allowable temperatures strictly constrained within 1, 373 K. Designing efficient and safe oil-cooled

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16

Zuo, Min, Zhen-Zong He, Shi-Jie Sun, Jun-Kui Mao, and Chuan-Hui Dong. "Simulation of flow and heat transfer characteristics of laminated turbine blades with kerosene cooling channels." Thermal Science, no. 00 (2023): 82. http://dx.doi.org/10.2298/tsci230115082z.

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An air-kerosene thermal mass coupled turbine blade with kerosene microchannels added to the traditional laminated structure turbine blade is proposed, and numerical simulations are carried out. The enhanced heat transfer mechanism of the air-kerosene thermal mass coupled turbine blade is studied, and the influence of different kerosene temperatures, blowing ratios, and solid thermal conductivity on the heat transfer of the laminated turbine blades is analyzed. The results show that adding kerosene microchannels can significantly reduce the blade temperature and change the cooling gas heat tran

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17

Burdet, André, and Reza S. Abhari. "Three-Dimensional Flow Prediction and Improvement of Holes Arrangement of a Film-Cooled Turbine Blade Using a Feature-Based Jet Model." Journal of Turbomachinery 129, no. 2 (2006): 258–68. http://dx.doi.org/10.1115/1.2437778.

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A feature-based jet model has been proposed for use in three-dimensional (3D) computational fluid dynamics (CFD) prediction of turbine blade film cooling. The goal of the model is to be able to perform computationally efficient flow prediction and optimization of film-cooled turbine blades. The model reproduces in the near-hole region the macroflow features of a coolant jet within a Reynolds-averaged Navier-Stokes framework. Numerical predictions of the 3D flow through a linear transonic film-cooled turbine cascade are carried out with the model, with a low computational overhead. Different co

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18

Tolu, Muhammed Emin, Osman Babayiğit, and Dilek Nur Özen. "INVESTIGATION OF THE EFFECTS OF RIB APPLICATION ON COOLING IN A TURBINE BLADE." Konya Journal of Engineering Sciences 13, no. 1 (2025): 11–24. https://doi.org/10.36306/konjes.1583865.

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Turbine blades are system components exposed to extremely high temperatures. Effective cooling of turbine blades is essential to enhance efficiency and extend the operational lifespan of gas turbines. In this study, a new rib turbulator cooling design was tested for the NASA C3X turbine blade. The analyses were compared with those conducted on non-ribbed blades. According to the findings, an average surface temperature of 574.6 K and a maximum surface temperature of 661.8 K were achieved. These values indicate a cooling efficiency of 19.1% for the leading edge, which is exposed to the maximum

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19

Torbidoni, Leonardo, and Aristide F. Massardo. "Analytical Blade Row Cooling Model for Innovative Gas Turbine Cycle Evaluations Supported by Semi-Empirical Air-Cooled Blade Data." Journal of Engineering for Gas Turbines and Power 126, no. 3 (2004): 498–506. http://dx.doi.org/10.1115/1.1707030.

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With the objective of performing reliable innovative gas turbine cycle calculations, a new procedure aimed at evaluating blade cooling performance is presented. This complete analytical (convective and film) blade cooling modeling provides the coolant mass flow and pressure loss estimation, and is a useful tool in the field of innovative gas turbine cycle analysis, mainly when alternative fluids are considered. In this case, in fact, the conventional semi-empirical data based on the use of air as traditional coolant and working media are no longer suitable. So the analytical approach represent

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Zhang, Yuanzhe, Pei Liu, and Zheng Li. "Impact of Cooling with Thermal Barrier Coatings on Flow Passage in a Gas Turbine." Energies 15, no. 1 (2021): 85. http://dx.doi.org/10.3390/en15010085.

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Inlet temperature is vital to the thermal efficiency of gas turbines, which is becoming increasingly important in the context of structural changes in power supplies with more intermittent renewable power sources. Blade cooling is a key method for gas turbines to maintain high inlet temperatures whilst also meeting material temperature limits. However, the implementation of blade cooling within a gas turbine—for instance, thermal barrier coatings (TBCs)—might also change its heat transfer characteristics and lead to challenges in calculating its internal temperature and thermal efficiency. Exi

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21

Elmenshawy, Adham Ahmed Awad Elsayed, Iyad Alomar, and Ali Arshad. "Optimization Turbine Blade Cooling by Applying Jet Impingement Cooling Channels." Transport and Telecommunication Journal 24, no. 3 (2023): 320–37. http://dx.doi.org/10.2478/ttj-2023-0026.

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Abstract The aim of this paper is to optimize turbine blade cooling channels by applying jet impingement Method. The selection of experiment data for NASA 3CX turbine blade, and 3D model using solidworks software and create computational fluid dynamics (CFD) simulations used to model the coolant flow and temperature distribution in the vane, while experimental testing can validate the CFD results and provide additional insights into the cooling system's performance., ANSYS FLUENT code was used as a CFD solver, and ANSYS ICEM-CFD was used for mesh generation. MATLAB code is used for calculation

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22

Hosseini, E. "Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD." Journal of Mechanical Engineering and Sciences 15, no. 1 (2021): 7637–47. http://dx.doi.org/10.15282/jmes.15.1.2021.02.0602.

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One way to achieve high performance in the gas turbine is to increase the inlet temperature of the turbine. Different cooling techniques have been carried out in order to protect the turbine blades which have been exposed to such high temperatures. Film cooling as an essential cooling method needs to be enhanced to meet the challenging demand. The purpose of the present research is to analyze the film cooling performance over a NACA 0012 gas turbine blade using six different injection holes with and without opening angles, separately through Computational Fluid Dynamics (CFD). 2D Reynolds-Aver

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23

Xi, Lei, Qicheng Ruan, Yuan Gao, Jianmin Gao, Liang Xu, and Yunlong Li. "Numerical study on cooling performance and thermal stress characteristic of an f-class gas turbine stator blade." Thermal Science, no. 00 (2024): 178. http://dx.doi.org/10.2298/tsci240422178x.

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In this study, a coupled numerical computation approach integrating aerothermal and thermomechanical effects was employed to investigate the cooling efficiency and thermal stress characteristics of gas turbine stator blades. A comprehensive analysis was conducted considering varying turbulence intensities in the coolant flow (spanning from 0.05 to 0.15) and different coolant media configurations, including pure air, dual-medium mixture of air and steam, and pure steam. The distributional traits of cooling efficiency and thermal stress on the stator blade surface under these conditions were met

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Christophel, J. R., K. A. Thole, and F. J. Cunha. "Cooling the Tip of a Turbine Blade Using Pressure Side Holes—Part I: Adiabatic Effectiveness Measurements." Journal of Turbomachinery 127, no. 2 (2005): 270–77. http://dx.doi.org/10.1115/1.1812320.

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Durability of turbine blade tips has been and continues to be challenging, particularly since increasing turbine inlet temperatures is the driver for improving turbine engine performance. As a result, cooling methods along the blade tip are crucial. Film-cooling is one typically used cooling method whereby coolant is supplied through holes placed along the pressure side of a blade. The subject of this paper is to evaluate the adiabatic effectiveness levels that occur on the blade tip through blowing coolant from holes placed near the tip of a blade along the pressure side. A range of blowing r

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Kim, Kyoung Hoon, Kyoung Jin Kim, and Hyung Jong Ko. "Effects of Wet Compression on Performance of Regenerative Gas Turbine Cycle with Turbine Blade Cooling." Applied Mechanics and Materials 224 (November 2012): 256–59. http://dx.doi.org/10.4028/www.scientific.net/amm.224.256.

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When water is injected at an inlet of compressor, wet compression occurs due to evaporation of water droplets. In this work, the effects of wet compression on the performance of regenerative gas turbine cycle with turbine blade cooling are analytically investigated. For various pressure ratios and water injection ratios, the important system variables such as ratio of coolant flow for turbine blade cooling, fuel consumption, specific power and thermal efficiency are estimated. Parametric studies show that wet compression leads to significant enhancement in both specific power and thermal effic

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26

Chrzanowski, Wojciech, Wojciech Napadłek, and Zdzisław Bogdanowicz. "Analysis of degradation and damage processes of power components of steam turbines." Bulletin of the Military University of Technology 72, no. 2 (2023): 39–63. http://dx.doi.org/10.5604/01.3001.0054.3655.

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The article is a review of the literature data related to the wear of steam turbine blades. The literature review have found that the main causes of blade damage are erosion, corrosion, and the occurrence of elevated temperatures inside the turbine, which cause, among other things, blade elongation, deformation, and cracks due to rapid temperature changes (thermal shock). A review of the literature has shown that blades are a subject to erosion resulting from operating conditions in which the blades strike water droplets formed from steam or from the injection of cooling condensate in the zone

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27

V S, Dr Ajith. "Design, Analysis and Material Optimization of Hybrid Cooling for Turbine Blades." International Journal for Research in Applied Science and Engineering Technology 13, no. 4 (2025): 2604–10. https://doi.org/10.22214/ijraset.2025.68786.

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The main goal of the study is to optimize the material and processes utilized in turbine blades to improve their performance and the cooling efficiency. The most relevant area of interest is the hybrid cooling which initiates the thermal management problems of air internal turbine blade cooling by combining it with film cooling. The design has been done using Catia V5 and SolidWorks which includes parameter definitions that result in enhanced optimized blade geometry which further augmented by the increased air cooling. It is also paramount that the shape, size and placement of the cooling hol

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Kolychev, A.V., M. Е. Renev, V. A. Savelov, and P. A. Arkhipov. "Effect of Vane Thermal Emission Cooling on the Efficiency of the Gas Turbine Power Plant." Problemele energeticii regionale 4, no. 48 (2020): 45–56. https://doi.org/10.5281/zenodo.4316996.

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The work is devoted to the problem of increasing efficiency of power gas turbine units (microturbines). One of ways to improve efficiency is to increase gas temperature in front of the turbine. Cooling of gas turbine elements is difficult. One of the solutions to the problem may be the method of thermal emission cooling. The purpose of this work is to estimate the potential effect of thermal emission cooling of turbine blades on efficiency. The mentioned aim is achieved by analyzing the main factors influencing the efficiency of the power gas turbine unit. Calculated estimations of thermal con

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Kim, Kyoung Hoon, Kyoung Jin Kim, and Chul Ho Han. "Comparative Thermodynamic Analysis of Gas Turbine Systems with Turbine Blade Film Cooling." Advanced Materials Research 505 (April 2012): 539–43. http://dx.doi.org/10.4028/www.scientific.net/amr.505.539.

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Since the gas turbine systems require active cooling to maintain high operating temperature while avoiding a reduction in the system operating life, turbine blade cooling is very important and essential but it may cause the performance losses in gas turbine. This paper deals with the comparative thermodynamic analysis of gas turbine system with and without regeneration by using the recently developed blade-cooling model when the turbine blades are cooled by the method of film cooling. Special attention is paid to investigating the effects of system parameters such as pressure ratio and turbine

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Xue, Song, and Wing Ng. "Turbine Blade Tip External Cooling Technologies." Aerospace 5, no. 3 (2018): 90. http://dx.doi.org/10.3390/aerospace5030090.

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This article provides an overview of gas turbine blade tip external cooling technologies. It is not the intention to comprehensively review all the publications from past to present. Instead, selected reports, which represent the most recent progress in tip cooling technology in open publications, are reviewed. The cooling performance on flat tip and squealer tip blades from reports are compared and discussed. As a generation conclusion, tip clearance dimension and coolant flow rate are found as the most important factors that significant influence the blade tip thermal performance was well as

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Chang, Shyy Woei, Pey-Shey Wu, Ting-Yu Wan, and Wei-Ling Cai. "A Review of Cooling Studies on Gas Turbine Rotor Blades with Rotation." Inventions 8, no. 1 (2023): 21. http://dx.doi.org/10.3390/inventions8010021.

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Increases in power density and thermal efficiency of a highly efficient gas turbine engine motivate an ever-mounting turbine entry temperature. The combined metallurgical and cooling advancements ensure the structural integrity of a gas turbine rotor blade that spins at high rotor speeds in a gas stream with temperatures above the melting point of the blade material. The cooling performances promoted by a variety of heat transfer enhancement methods typical of the coolant channels of the leading edge, the mid-chord region, and the trailing edge of a gas turbine rotor blade are reviewed. The ma

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Naas, Toufik Tayeb, Mostefa Telha, Ismail Ghibeche, Omar Mokhtar Khelifa, and Salem Ben Abdelhafid. "Cooling Efficiency of a NACA4412 airfoil: Numerical application." STUDIES IN ENGINEERING AND EXACT SCIENCES 5, no. 1 (2024): 906–25. http://dx.doi.org/10.54021/seesv5n1-048.

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The temperatures imposed on the blades of the first stages of turbines are generally very high; these expose the latter to harmful thermal effects, pushing manufacturers to continually improve techniques for cooling the blades. It is true that by increasing the temperature of the gases at the inlet of the turbines, we increase the efficiency, the performance of the machines, and we improve the power and fuel consumption with a significant reduction in polluting gases. Thus, the current general trend among manufacturers is to design machines that operate at increasingly high inlet temperatures.

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PAVLOV, N. S., V. V. BARSKOV, M. A. LAPTEV, M. A. GOLUBTSOV, I. R. NURKOV, and K. A. ALISOV. "ANALYSIS OF THE TEMPERATURE STATE OF THE COOLED TURBINE BLADE OF HIGH POWER DURING THE TRANSITION FROM AIR TO STEAM COOLING." Turbines & Diesels, no. 6 (2024): 26–30. https://doi.org/10.70195/2949-2971-2024-0-6-26-30.

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Recently, our country has been actively creating a line of its own gas turbines. Along with the development and commissioning of mass production of domestic high-power GTP, the relevance of researching possible options for upgrading such turbines is increasing, one of which is cooling the hot path of the turbine unit, which reduces thermal loads of the body, thereby increasing the resource and efficiency of operation. A promising method is steam cooling, which is able to absorb more heat by changing the aggregate state. The article presents the results of a study of the effect of the cooler ty

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Khudheyer, Ahmed F., and Hussein T. Dhaiban. "Numerical Study Of Heat Transfer In Cooling Passages Of Turbine Blade." Journal of Engineering 19, no. 3 (2023): 342–56. http://dx.doi.org/10.31026/j.eng.2013.03.05.

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As the temperature of combustion gases is higher than the melting temperature of the turbine materials, cooling of turbine parts in a gas turbine engine is necessary for safe operation. Cooling methods investigated in this computational study included cooling flow losses. Film-cooling is one typically used cooling method whereby coolant is supplied through holes passage, in present study the holes placed along the camber line of the blade. The subject of this paper is to evaluate the heat transfer that occur on the holes of blade through differentblowing coolant rates. The cases of this study

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Aizon, W. Ghopa Wan, and Kenichi Funazaki. "Aero-Thermal Performance of Purge Flow in Turbine Cascade Endwall Cooling." Applied Mechanics and Materials 229-231 (November 2012): 737–41. http://dx.doi.org/10.4028/www.scientific.net/amm.229-231.737.

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The endwall and blade film cooling systems are the typical solution adopted within gas turbines to allow further increase of turbine inlet temperature, avoiding critical material thermal stresses. Due to complex secondary flow field in the blade passage, endwallis more difficult to cool than blade surfaces. In the matter of fact, in endwall film cooling studies, it is necessary to investigate the interaction between coolant air and the secondary flow. In present study, the flow field of high-pressure turbine cascade has been investigated by 5-holes pitot tube to reveal the secondary flows beha

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Power, D. C. "Palladium Alloy Pinning Wires for Gas Turbine Blade Investment Casting." Platinum Metals Review 39, no. 3 (1995): 117–26. http://dx.doi.org/10.1595/003214095x393117126.

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Turbine blades in aero-engine and land-based power generation gas turbines are complex components manufactured to precise geometric, structural and machanical property tolerances. High pressure turbine blades used in the hottest, most hostile and demanding sections of gas turbines often contain integral cooling channels. The production of such cooling channels has been a significant advance in gas turbine efficiency and emission control. Pinning wires are used during mould preparation and investment casting of the blades for reliable manufacture of the cooling channels. Traditional platinum-ba

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El-Oun, Z. B., and J. M. Owen. "Preswirl Blade-Cooling Effectiveness in an Adiabatic Rotor–Stator System." Journal of Turbomachinery 111, no. 4 (1989): 522–29. http://dx.doi.org/10.1115/1.3262303.

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Blade-cooling air for a high-pressure turbine is often supplied from preswirl nozzles attached to a stationary casing. By swirling the cooling air in the direction of rotation of the turbine disk, the temperature of the air relative to the blades can be reduced. The question addressed in this paper is: Knowing the temperatures of the preswirl and disk-cooling flows, what is the temperature of the blade-cooling air? A simple theoretical model, based on the Reynolds analogy applied to an adiabatic rotor–stator system, is used to calculate the preswirl effectiveness (that is, the reduction in the

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Deepak, Dewangan* Ajay Kumar Verma. "NUMERICAL INVESTIGATION OF TURBINE BLADE COOLING PASSAGE WITH V-SHAPE TRUNCATED AND CONTINEOUS RIBS." INTERNATIONAL JOURNAL OF ENGINEERING SCIENCES & RESEARCH TECHNOLOGY 5, no. 7 (2016): 36–48. https://doi.org/10.5281/zenodo.56891.

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This paper focus on 3D CFD analysis of an turbine blade cooling passage/duct in which the desired domain subjected to critical load i.e. static as well as dynamic load which is due turbine blade is operated at high temperature and pressure which results in thermal stress and alters the blade performance. In order to avoid clastatic failure of blade effective and efficient cooling techniques should be implemented which ultimately results in higher thermal efficiency and maximum power output. Extensive literature review is carried out in the field relating to turbine blade cooling. This work is

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Niranjan, B. Ghule, and Rai Prayass. "NUMERICAL STUDY OF TURBINE BLADE FILM COOLING TECHNOLOGY." JournalNX - a Multidisciplinary Peer Reviewed Journal TDCME-2k18 (May 11, 2018): 194–98. https://doi.org/10.5281/zenodo.1420080.

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In order to increase thermal efficiency of a gas turbine, higher turbine inlet temperature (TIT) is needed. However, higher TIT increases thermal loading to its hot-section components and reducing their life. Therefore, one of the very complicated cooling technology such as film cooling and internal cooling is required especially for HP turbine blades. In film cooling, relatively cool air is injected onto the turbine blade surface to form a protective layer between the surface and hot mainstream gas. The highest thermal load usually occurs at the leading edge of the airfoil, and failure is pro

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Li, Pengfei, Jianmei Guo, Yanhua Cai, et al. "A positioning correction method for turbine blade film cooling holes." Journal of Physics: Conference Series 2365, no. 1 (2022): 012008. http://dx.doi.org/10.1088/1742-6596/2365/1/012008.

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Abstract It is significant to improve the machining accuracy of film cooling holes on aero-engine turbine blades. This paper presents a method to correct the position of film cooling holes on turbine blades. In this method, the pre-positioning algorithm and the precise positioning algorithm are proposed. The pre-positioning algorithm introduces the blade structure information. In the precise positioning algorithm, 3D coordinate transformation, ∠B and ∠C of 5-axis machine tool updating, iteration points creating based on the normal vector are designed. The operation of the gas film cooling hole

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Zhu, Shixing, Yan Li, Junyang Yan, and Chao Zhang. "Recent Advances in Cooling Technology for the Leading Edge of Gas Turbine Blades." Energies 18, no. 3 (2025): 540. https://doi.org/10.3390/en18030540.

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As the inlet temperature of the gas turbine exceeds the high temperature limit of the blade materials, efficient leading edge cooling technologies are crucial for the further development of gas turbines. Therefore, this paper reviews the research progress on external cooling technology, internal cooling technology, and composite cooling technology for gas turbine rotating blade leading edge cooling. It focuses on the impact of the geometric shape, arrangement, and flow parameters of film cooling holes on external cooling performance, the influence of jet hole design, configuration, crossflow,

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Mahboob, Shaheen. "Structural Analysis & Effect of Impingement Cooling Flow in the Internal Surface on Temperature Distribution of a Vane in Gas Turbine Using Taguchi Technique." International Journal for Research in Applied Science and Engineering Technology 12, no. 4 (2024): 3835–42. http://dx.doi.org/10.22214/ijraset.2024.60775.

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Abstract: Gas turbine always consider one of the most important systems in the modern engineering applications, because it has continuous ability to generate electric power. In gas turbines the major portion of performance dependency lies upon turbine blade design ,the blades are considered one of the important and expensive parts in the gas turbines , where the blades of first stage from failure .The blades of the gas turbine suffer from tensile stresses due to centrifugal forces resulting from the high rotational speed and because of the loading of densegasses at a high temperature and speed

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Molyakov, V. D., and B. A. Kunikeev. "Using the Similarity Theory in the Design of Gas Turbine Engines." Proceedings of Higher Educational Institutions. Маchine Building, no. 6 (735) (June 2021): 48–57. http://dx.doi.org/10.18698/0536-1044-2021-6-48-57.

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At present, in the promising development of gas turbine engines compared to at least the fourth generation products, there have been significant changes in the approaches to the design of engine. First of all, it is an increase in maximum values of temperature, gas pressure and circumferential flow speeds, an increase in power of the turbine stage, as well as improvement of the turbine manufacturing technology. All these factors lead to the fact that when designing the flow parts of the gas turbine, it is necessary at the fixed design flow rate of the working medium in the engine, i.e. at the

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Rantai, Romesh, Alok Sharma, and Vikky Kumhar. "Comparative CFD Analysis of Forced Convection Cooling of a Gas Turbine Blade of Different Materials with Several Staggered holes." INTERANTIONAL JOURNAL OF SCIENTIFIC RESEARCH IN ENGINEERING AND MANAGEMENT 07, no. 09 (2023): 1–11. http://dx.doi.org/10.55041/ijsrem25721.

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For gas turbines, the energy of the fluid can be expressed in terms of the enthalpy change, which is almost directly related to the turbine temperature. The performance of the gas turbine can be improved by continuously improving the temperature and compression ratio. In this article, for the cooling of blades, making several radial holes has been suggested to pass high cooling air at high velocity along the span of blade. CFD analysis has been used to analyse the effect of heat transfer of a gas turbine with six different models which has 6,7,8,9,10,11,12 inline one row of holes and are furth

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Schobeiri, M. T., and K. Pappu. "Optimization of Trailing Edge Ejection Mixing Losses: A Theoretical and Experimental Study." Journal of Fluids Engineering 121, no. 1 (1999): 118–25. http://dx.doi.org/10.1115/1.2821991.

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The aerodynamic effects of trailing edge ejection on mixing losses downstream of cooled gas turbine blades were experimentally investigated and compared with an already existing one-dimensional theory by Schobeiri (1989). The significant parameters determining the mixing losses and, therefore, the efficiency of cooled blades, are the ejection velocity ratio, the cooling mass flow ratio, the temperature ratio, the slot thickness ratio, and the ejection flow angle. To cover a broad range of representative turbine blade geometry and flow deflections, a General Electric power generation gas turbin

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Sun, Huayang, Xinlong Yang, Yingtao Chen, Yanting Ai, and Wanlin Zhang. "Study on the Impact of Cooling Air Parameter Changes on the Thermal Fatigue Life of Film Cooling Turbine Blades." Aerospace 12, no. 6 (2025): 512. https://doi.org/10.3390/aerospace12060512.

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Film cooling has been increasingly applied in turbine blade cooling design due to its excellent cooling performance. Although film-cooled blades demonstrate superior cooling effectiveness, the perforation design on blade surfaces compromises structural integrity, making fatigue failure prone to occur at cooling holes. Previous studies by domestic and international scholars have extensively investigated factors influencing film cooling effectiveness, including blowing ratio and hole geometry configurations. However, most research has overlooked the investigation of fatigue life in film-cooled b

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Dai, Ping, and Shuang Xiu Li. "Recent Advances in the Study of Film Cooling on the Gas Turbine Blade." Advanced Materials Research 971-973 (June 2014): 143–47. http://dx.doi.org/10.4028/www.scientific.net/amr.971-973.143.

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The development of a new generation of high performance gas turbine engines requires gas turbines to be operated at very high inlet temperatures, which are much higher than the allowable metal temperatures. Consequently, this necessitates the need for advanced cooling techniques. Among the numerous cooling technologies, the film cooling technology has superior advantages and relatively favorable application prospect. The recent research progress of film cooling techniques for gas turbine blade is reviewed and basic principle of film cooling is also illustrated. Progress on rotor blade and stat

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Ranson, W. W., K. A. Thole, and F. J. Cunha. "Adiabatic Effectiveness Measurements and Predictions of Leakage Flows Along a Blade Endwall." Journal of Turbomachinery 127, no. 3 (2005): 609–18. http://dx.doi.org/10.1115/1.1929809.

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Traditional cooling schemes have been developed to cool turbine blades using high-pressure compressor air that bypasses the combustor. This high-pressure forces cooling air into the hot main gas path through seal slots. While parasitic leakages can provide a cooling benefit, they also represent aerodynamic losses. The results from the combined experimental and computational studies reported in this paper address the cooling benefit from leakage flows that occur along the platform of a first stage turbine blade. A scaled-up, blade geometry with an upstream slot, a mid-passage slot, and a downst

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Gibson, Tom, and Thomas Romer. "Additive Advantage." Mechanical Engineering 139, no. 12 (2017): 35. http://dx.doi.org/10.1115/1.2017-dec-4.

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This article describes the basic features of a 3D printed blade that can survive inside a turbine. This blade has been developed by Siemens. The team behind the blade included project manager, Jenny Nilsson, as well as engineers at Material Solutions, a company Siemens later bought. Team members developed better cooling designs to improve the gas turbine efficiency, designed the blade, and developed the whole manufacturing process to manufacture this type of component and geometry. Like all additive manufacturing, the team applied thin layers of material—one after the other—to build up a finis

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Kim, T. S., and S. T. Ro. "The effect of gas turbine coolant modulation on the part load performance of combined cycle plants. Part 1: Gas turbines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 211, no. 6 (1997): 443–51. http://dx.doi.org/10.1243/0957650981537339.

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This paper demonstrates a favourable influence of turbine coolant modulation on the part load performance of gas turbines. A general simulation programme is developed, which is capable of accurately estimating the design and part load performance of modern heavy-duty gas turbines characterized by intensive turbine blade cooling Investigations are made for a typical gas turbine and two distinct load control schemes are considered: the fuel-only control and the variable compressor geometry control. Maintaining blade temperatures as high as possible whose purpose is to minimize coolant consumptio

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