Relevant bibliographies by topics / Turbine blade cooling

Contents

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

Academic literature on the topic 'Turbine blade cooling'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 July 2025

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Journal articles on the topic "Turbine blade cooling"

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

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

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Barry, Pamela S. (Pamela Sue). "Rotational effects on turbine blade cooling." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/12114.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1994.<br>Title as it appears in the June 1994 MIT Graduate List: Rotational effects of turbine cooling.<br>Includes bibliographical references (leaves 102-103).<br>by Pamela S. Barry.<br>M.S.
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Ryley, Joshua Claydon. "Turbine blade mid-chord internal cooling." Thesis, University of Oxford, 2014. http://ora.ox.ac.uk/objects/uuid:14469a51-517c-400c-b477-4fb432c8b648.

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Modern gas turbine engines operate at temperatures well above the melting point of the metal components. This has driven manufactures to develop sophisticated cooling methods which minimise the use of coolant to maximise engine efficiency by enabling further increases in operating temperature. This thesis investigates the cooling performance of engine representative mid-chord internal cooling passages for turbine blades. The work forms part of a larger E.C. FP7 project ERICKA (Engine Representative Internal Cooling Knowledge Applications).This thesis provides detailed maps of heat transfer coe
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Telisinghe, Janendra C. "Film cooling of turbine blade trailing edges." Thesis, University of Oxford, 2013. http://ora.ox.ac.uk/objects/uuid:86c06246-16e9-4378-9a61-e09317d31a92.

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In modern gas turbine engines, film cooling is extensively used to cool the components exposed to the hot mainstream gas path. In implementing film cooling on modern gas turbine engines, the trailing edge film poses a particularly challenging design problem. From an aerodynamic point of view, the trailing edge of a blade is designed to be as thin as possible. However, this conflicts with the implementation of the cooling design. The most common method of film cooling the trailing edge is via late pressure surface discrete film cooling holes. Another method of cooling the trailing edge is by us
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Choi, Jungho. "An experimental investigation of turbine blade heat transfer and turbine blade trailing edge cooling." Texas A&M University, 2004. http://hdl.handle.net/1969.1/1377.

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This experimental study contains two points; part1 – turbine blade heat transfer under low Reynolds number flow conditions, and part 2 – trailing edge cooling and heat transfer. The effect of unsteady wake and free stream turbulence on heat transfer and pressure coefficients of a turbine blade was investigated in low Reynolds number flows. The experiments were performed on a five blade linear cascade in a low speed wind tunnel. A spoked wheel type wake generator and two different turbulence grids were employed to generate different levels of the Strouhal number and turbulence intensity, respec
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Joo, Jongwook. "Eddy simulation of turbine blade trailing edge cooling /." May be available electronically:, 2008. http://proquest.umi.com/login?COPT=REJTPTU1MTUmSU5UPTAmVkVSPTI=&clientId=12498.

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Chambers, Andrew. "An investigation of impingement cooling applied to turbine blade cooling passages." Thesis, University of Oxford, 2003. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.400071.

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Fransen, Rémy. "LES based aerothermal modeling of turbine blade cooling systems." Phd thesis, Toulouse, INPT, 2013. http://oatao.univ-toulouse.fr/10012/1/fransen.pdf.

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This PhD dissertation, conducted as part of a CIFRE research project between TURBOMECA and CERFACS in partnership with the VKI, deals with improving performance of axial turbines from helicopter engines. One of the most critical design points of such engines is the control of the high pressure turbine blade lifetime which face the high temperatures from the combustor. Today, industrial numerical aerothermal predictions of the flows around the blade (in the vein and in its cooling system) are performed with the Reynolds Averaged Navier-Stokes (RANS). Thanks to the increasing computational power
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Long, K. "Aluminide-based coatings for turbine blade internal cooling passages." Thesis, Cranfield University, 2004. http://dspace.lib.cranfield.ac.uk/handle/1826/11002.

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The development of aero-gas turbines is moving towards more efficient engines with higher pressure ratios and increased Turbine Entry Temperatures. This leads to increases in overall turbine blades temperatures which has resulted in the widescale development of turbine blades with film cooling and Thermal Barrier Coatings (TBCs) which reduce the metal temperature of the blade. The air used for film cooling is directed around the blade by internal passages within the blade, current engines are experiencing hot corrosion in areas of these internal passages, even with internal aluminide coatings.
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Tang, Brian M. T. "Unshrouded turbine blade tip heat transfer and film cooling." Thesis, University of Oxford, 2011. http://ora.ox.ac.uk/objects/uuid:f8479e89-9cd1-4aa7-b5c8-8068ad80de54.

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This thesis presents a joint computational and experimental investigation into the heat transfer to unshrouded turbine blade tips suitable for use in high bypass ratio, large civil aviation turbofan engines. Both the heat transfer to the blade tip and the over-tip leakage flow over the blade tip are characterised, as each has a profound influence on overall engine efficiency. The study is divided into two sections; in the first, computational simulations of a very large scale, low speed linear cascade with a flat blade tip were conducted. These simulations were validated against experimental d
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Gillespie, David R. H. "Intricate internal cooling systems for gas turbine blading." Thesis, University of Oxford, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365831.

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Books on the topic "Turbine blade cooling"

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Ghodke, Chaitanya D. Gas Turbine Blade Cooling. SAE International, 2018. http://dx.doi.org/10.4271/0768095069.

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Ghodke, Chaitanya. Gas Turbine Blade Cooling. SAE International, 2018. http://dx.doi.org/10.4271/pt-196.

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Noot, Marc. Numerical analysis of turbine blade cooling ducts. Eindhoven University, 1997.

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Garg, Vijay Kumar. Leading edge film cooling effects on turbine blade heat transfer. National Aeronautics and Space Administration, 1995.

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N, Tse D. G., and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. A combined experimental/computational study of flow in turbine blade cooling passage. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1994.

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-N, Tse D. G., and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. A combined experimental/computational study of flow in turbine blade cooling passage. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1994.

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United States. National Aeronautics and Space Administration., ed. A numerical study of the effect of wake passing on turbine blade film cooling. National Aeronautics and Space Administration, 1995.

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M, Russell Louis, and Lewis Research Center, eds. Measurements of heat transfer, flow, and pressures in a simulated turbine blade internal cooling passage. National Aeronautics and Space Administration, Lewis Research Center, 1997.

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M, Russell Louis, and Lewis Research Center, eds. Measurements of heat transfer, flow, and pressures in a simulated turbine blade internal cooling passage. National Aeronautics and Space Administration, Lewis Research Center, 1997.

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M, Russell Louis, and United States. National Aeronautics and Space Administration., eds. Measurements and computational analysis of heat transfer and flow in a simulated turbine blade internal cooling passage. National Aeronautics and Space Administration, 1993.

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Book chapters on the topic "Turbine blade cooling"

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Stania, Lennart, and Joerg R. Seume. "Regeneration-Induced Variances of Aeroelastic Properties of Turbine Blades." In Regeneration of Complex Capital Goods. Springer International Publishing, 2024. http://dx.doi.org/10.1007/978-3-031-51395-4_15.

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AbstractRegeneration and wear result in geometric deviations between design intent and reality of turbine blades. These deviations influence the aerodynamic flow field and the aeroelastic behaviour of downstream blades. As an example for the effect of such deviations between modules on blade vibration amplitudes, an experiment is set up to determine the influence of cold streaks, which can occur due to widening of cooling air holes. The vibration amplitude for an off-design point is increased by 20% and for the design point as well. We conclude that the forced response caused by cooling air fr
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Srinivasan, P., and M. Yogi Aditya. "CFD Based Study of Gas Turbine Blade Cooling." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-7055-9_51.

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Tamang, Sajan, and Heesung Park. "Effect of Mist Size on the Cooling Performance for Internal Cooling of Gas Turbine Blade." In Lecture Notes in Mechanical Engineering. Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-66609-4_67.

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Wang, M., Di Zhu, N. S. Qu, and C. Y. Zhang. "Preparation of Turbulated Cooling Hole for Gas Turbine Blade Using Electrochemical Machining." In Advances in Abrasive Technology IX. Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-416-2.699.

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Mohammed Aashiq, S., R. Sabarishwaran, K. M. Parammasivam, M. Ramesh, and R. Reju. "Experimental and Computational Investigation on Film Cooling Effectiveness of Turbine Stator Blade." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6970-6_29.

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Nguyen, Tien-Dung, Hai-Quang Do, Cong-Hung Hoang, et al. "Effect of Turning Vanes on Heat Exchange Characteristics of Cooling Channel in Turbine Blade." In The AUN/SEED-Net Joint Regional Conference in Transportation, Energy, and Mechanical Manufacturing Engineering. Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1968-8_100.

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Purnadiana, Farida Rahmawati, Prabowo, and Herman Sasongko. "The Performance Comparison Between Modelled and Fully Simulated Porous Media in Turbine Blade Cooling." In Lecture Notes in Electrical Engineering. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-97-8197-3_4.

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Basha, Moughbul, and Mithilesh Kumar Sahu. "CFD Analysis of Twisted Gas Turbine Blade with Different Cooling Hole Geometries on Leading Edge." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-4165-4_43.

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Suryo, Is Bunyamin, Firlana Baiturrochman, Even Clarence, Farida Rahmawati Purnadiana, and Stefano Johanes Tanod. "Numerical Study on the Effect of Modification Internally Cooling Passages of NASA C3X Turbine Blade." In Lecture Notes in Electrical Engineering. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-97-8197-3_38.

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Li, Shaohua, Tao Peng, Li-xian Liu, Ting-ting Guo, and Bin Yuan. "Numerical Simulation of Turbine Blade Film-cooling with Different Blowing Ratio and Hole-to-hole Space." In Challenges of Power Engineering and Environment. Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-76694-0_258.

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Conference papers on the topic "Turbine blade cooling"

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Tao, Zhi, Haiwang Li, and Ruquan You. "TURBINE BLADE COOLING AT BUAA." In International Heat Transfer Conference 16. Begellhouse, 2018. http://dx.doi.org/10.1615/ihtc16.kn.000027.

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Huang, Qihe, Jiao Wang, Lei He, and Qiang Xu. "Numerical Study of Heat Transfer and Cooling Effectiveness on a Flat-Tip Turbine Blade." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2053.

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A numerical study is performed to simulate the tip leakage flow and heat transfer on the first stage rotor blade tip of GE-E3 turbine, which represents a modern gas turbine blade geometry. Calculations consist of the flat blade tip without and with film cooling. For the flat tip without film cooling case, in order to investigate the effect of tip gap clearance on the leakage flow and heat transfer on the blade tip, three different tip gap clearances of 1.0%, 1.5% and 2.5% of the blade span are considered. And to assess the performance of the turbulence models in correctly predicting the blade
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Tamunobere, Onieluan, and Sumanta Acharya. "Turbine Blade Tip Cooling With Blade Rotation: Part II — Shroud Coolant Injection." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42564.

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In this paper, blade-tip cooling is investigated with coolant injection from the shroud alone and a combination of shroud coolant injection and tip cooling. The blade rotates at a nominal speed of 1200 RPM, and consists of a cut back squealer tip with a tip clearance of 1.7% of the blade span. The blade consists of tip holes and pressure side shaped holes, while the shroud has an array of angled holes and a circumferential slot upstream of the rotor section. Different combinations of the three cooling configurations are utilized to study the effectiveness of shroud cooling as a complementary m
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Mamaev, B. I., M. M. Petukhovsky, and A. V. Pozdnyakov. "Shrouding the First Blade of High Temperature Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2001.

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Blade shrouding gives an opportunity to increase the HPT (high pressure turbine) first stage efficiency by 2–3 %. However, if high gas temperature and high circumferential velocity are at the stage, shrouding can be problematic due to load increasing at blade/disk attachment and high temperature of the shroud itself. To make blade/disk attachment more reliable the shroud axial width has to be decreased by increasing a relative pitch of airfoil cascades t (t = t / b, where t – pitch, b – chord) at the blade tip span. According to experience for a flow with β1 = 50 – 85°, M2 = 0.8 – 1, and Re =
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Ledezma, G. A., J. Allen, and R. S. Bunker. "An Experimental and Numerical Investigation Into the Effects of Squealer Blade Tip Modifications on Aerodynamic Performance." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2004.

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Gas turbine blades using the so-called squealer tip configuration represent a majority of the high-pressure first stage blades in service. The squealer tip in its most basic format is simply a two-tooth labyrinth seal projecting from the blade tip towards the stationary shroud or casing. As with all blade tip configurations, the geometry is a compromise between aerodynamics, cooling, mechanical stress, durability, and repair. While many proposed blade tip innovations involve more complex geometries, this study seeks to determine if a simpler geometry, other than a flat tip, can provide equival
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Rademaker, Edward R., Rob A. Huls, Bambang I. Soemarwoto, and Ron van Gestel. "Modeling Approach to Calculate Redistributions of HPT-Shroud Cooling Channels Minimizing Thermal Stresses Including Some Turbine Blade Tip Effects." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2060.

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A numerical case study on a HPT-shroud of a medium-sized commercial engine has been carried out to investigate the heat loading and the possible redistribution (number of channels, position and exit angle) of shroud cooling channels facing the turbine blade tip. A combination of modeling vehicles was used to quantify the aerodynamics, the thermodynamics and resulting heat loads on the shroud. This includes a 1-D gas turbine performance simulation model, engineering models for cooling flow distributions and heat loads, CFD modeling of the HPT flow including some tip flow effects and the finite
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Wright, Lesley M., and Je-Chin Han. "Heat Transfer Enhancement for Turbine Blade Internal Cooling." In ASME 2013 Heat Transfer Summer Conference collocated with the ASME 2013 7th International Conference on Energy Sustainability and the ASME 2013 11th International Conference on Fuel Cell Science, Engineering and Technology. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/ht2013-17813.

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Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. The turbine inlet temperatures are far above the permissible metal temperatures. Therefore, there is a need to cool the blades for safe operation. Modern developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced gas turbine designs. Turbine blades and vanes are cooled internally and externally. This paper focuses on heat transfer augmentation of turbine blade internal cooling. Internal cooling is typically a
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Huh, Michael, and Je-Chin Han. "RECENT STUDIES IN TURBINE BLADE INTERNAL COOLING." In TURBINE-09. Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems. Begellhouse, 2009. http://dx.doi.org/10.1615/ichmt.2009.heattransfgasturbsyst.460.

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Sanaye, Sepehr, and Mehdi Darvishi. "Thermodynamic Modeling of Gas Turbine Blade Cooling." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-28298.

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Gas turbines are widely used in various industries and the thermal modeling of this equipment is of primary interest to predict its operating condition. One of reasons for deviation of numerical values obtained for actual gas turbine performance and the results obtained from thermal modeling is the effects of blade cooling. In this paper, three blade-cooling models are studied. The first one is the El-Masri continuous model which later modified by Bolland and De Paepe. The Jordal stage-by-stage model and Walsh &amp; Fletcher model are the second and third blade cooling models studied here. The
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Yunfeng, Zhao. "Study on turbine blade fractures of some cooling turbine." In 2016 IEEE/CSAA International Conference on Aircraft Utility Systems (AUS). IEEE, 2016. http://dx.doi.org/10.1109/aus.2016.7748216.

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Reports on the topic "Turbine blade cooling"

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Cao, Yiding. An Innovative Turbine Blade Cooling Technology and Micro/Miniature Heat Pipes for Turbine Blades. Defense Technical Information Center, 2000. http://dx.doi.org/10.21236/ada381455.

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Raben, Sam, Pavlos Vlachos, and Wing Ng. Effects of Leading Edge Film-Cooling and Surface Roughness on the Downstream Film-Cooling Along a Transonic Turbine Blade for Low and High Free-Stream Turbulence. Defense Technical Information Center, 2008. http://dx.doi.org/10.21236/ada479415.

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Schumacher. PR-333-06202-R01 Ultrasonic Inspection of RB211-24C Blades. Pipeline Research Council International, Inc. (PRCI), 2012. http://dx.doi.org/10.55274/r0010756.

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Abstract:
The service lives of RB211-24C HP turbine blades are limited by the formation of cracks on the cooling passages. Currently the presence of such cracking is determined by the destructive evaluation of several blades from each set when they are removed from service. The objective of this project was to develop a non-destructive inspection technique capable of detecting cracks on the surfaces of RB211-24C HP blades.
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