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Relevant bibliographies by topics / "turbine blade tip rub"

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Academic literature on the topic '"turbine blade tip rub"'

Author: Grafiati

Published: 4 June 2021

Last updated: 10 February 2022

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Journal articles on the topic ""turbine blade tip rub""

1

Padova, Corso, Jeffrey Barton, Michael G. Dunn, et al. "Development of an Experimental Capability to Produce Controlled Blade Tip∕Shroud Rubs at Engine Speed." Journal of Turbomachinery 127, no. 4 (2004): 726–35. http://dx.doi.org/10.1115/1.1934429.

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An experimental capability using an in-ground spin-pit facility specifically designed to investigate aeromechanic phenomena for gas turbine engine hardware rotating at engine speed is demonstrated herein to obtain specific information related to prediction and modeling of blade-casing interactions. Experiments are designed to allow insertion of a segment of engine casing into the path of single-bladed or multiple-bladed disks. In the current facility configuration, a 90deg sector of a representative engine casing is forced to rub the tip of a single-bladed compressor disk for a selected number

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Satish, TN, A. Vivek, SN Anagha, et al. "Novel resistor-capacitor (RC) network-based capacitance signal conditioning circuit for tip clearance measurement on gas turbine engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 2 (2019): 342–60. http://dx.doi.org/10.1177/0954410019865853.

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Blade tip clearance is a critical engine health parameter measured on gas turbines. Increase in tip clearance results in decreased efficiency, whereas with decrease in clearance due to thermal and centrifugal loads, rotor blades might rub the engine case. Various sensing techniques are being used, among them, capacitance-based systems are widely used by many engine houses. Among the capacitance conditioning circuits, resistor-capacitor series network-based circuits are simple to implement but pose many challenges during practical development. During the current work, the authors have designed

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Tong, Fujuan, Wenxuan Gou, Lei Li, Zhufeng Yue, Wenjing Gao, and Honglin Li. "Numerical investigation of high pressure turbine blade tip-shaping effects on the aerothermal and dynamic performance." Multidiscipline Modeling in Materials and Structures 15, no. 6 (2019): 1121–35. http://dx.doi.org/10.1108/mmms-03-2019-0053.

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Purpose In order to improve the engine reliability and efficiency, an effective way is to reform the turbine blade tip conformation. The paper aims to discuss this issue. Design/methodology/approach The present research provides several novel tip-shaping structures, which are considered to control the blade tip loss. Four different tip geometries have been studied: flat tip, squealer tip, flat tip with streamwise ribs and squealer tip with streamwise ribs. The tip heat transfer and leakage flow are both analyzed in detail, for example the tip heat transfer coefficient, tip flow and local press

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Nielsen, Mikkel Schou, Ivan Nikolov, Emil Krog Kruse, Jørgen Garnæs, and Claus Brøndgaard Madsen. "High-Resolution Structure-from-Motion for Quantitative Measurement of Leading-Edge Roughness." Energies 13, no. 15 (2020): 3916. http://dx.doi.org/10.3390/en13153916.

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Over time, erosion of the leading edge of wind turbine blades increases the leading-edge roughness (LER). This may reduce the aerodynamic performance of the blade and hence the annual energy production of the wind turbine. As early detection is key for cost-effective maintenance, inspection methods are needed to quantify the LER of the blade. The aim of this proof-of-principle study is to determine whether high-resolution Structure-from-Motion (SfM) has the sufficient resolution and accuracy for quantitative inspection of LER. SfM provides 3D reconstruction of an object geometry using overlapp

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Jiang, Shijie, Zhigang Li, Jun Li, and Liming Song. "Effects of the novel rib layouts on the tip leakage flow pattern and heat transfer performance of turbine blade." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 8 (2020): 1446–59. http://dx.doi.org/10.1177/0954410020910883.

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The steady simulation with flow field and heat transfer performance for different rib layouts is investigated. By referring the GE-E3 turbine blade tip (Case 1) profile as a prototype model, four kinds of rib layouts of full rib structure (Case 2), half rib structure connected with suction side (Case 3), half rib structure connected with pressure side (Case 4), and half rib structure in the rear squealer cavity (Case 5) was designed. The availability of k-ω turbulence model was validated through comparison of heat transfer coefficient distribution with the experimental data. The area-averaged

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Lee, Byung Ju, Kun Sung Park, Jin Young Jeong, Jae Su kwak, and Jin Taek Chung. "Numerical Investigation on Effects of Rib or Cavity Design of Gas Turbine Blade Tip on the Flow and Heat Transfer Characteristics near Tip Region." KSFM Journal of Fluid Machinery 24, no. 3 (2021): 5–14. http://dx.doi.org/10.5293/kfma.2021.24.3.005.

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Sewall, Evan A., and Danesh K. Tafti. "Large Eddy Simulation of Flow and Heat Transfer in the 180‐Deg Bend Region of a Stationary Gas Turbine Blade Ribbed Internal Cooling Duct." Journal of Turbomachinery 128, no. 4 (2005): 763–71. http://dx.doi.org/10.1115/1.2098769.

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Large eddy simulation of the 180 deg bend in a stationary ribbed duct is presented. The domain studied includes three ribs upstream of the bend region and three ribs downstream of the bend with an outflow extension added to the end, using a total of 8.4 million cells. Two cases are compared to each other: one includes a rib in the bend and the other does not. The friction factor, mean flow, turbulence, and heat transfer are compared in the two cases to help explain the benefits and disadvantages of the wide number of flow effects seen in the bend, including flow separation at the tip of the di

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Zhang, Bo-lun, Hui-ren Zhu, Chun-yi Yao, and Cun-liang Liu. "Investigation on aerothermal performance of a rib-slot scheme on the multi-cavity tip of a gas turbine blade." International Journal of Heat and Mass Transfer 176 (September 2021): 121408. http://dx.doi.org/10.1016/j.ijheatmasstransfer.2021.121408.

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Hong, Jie, Tianrang Li, Zhichao Liang, Dayi Zhang, and Yanhong Ma. "Research on Blade-Casing Rub-Impact Mechanism by Experiment and Simulation in Aeroengines." Shock and Vibration 2019 (April 22, 2019): 1–15. http://dx.doi.org/10.1155/2019/3237960.

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Aeroengines pursue high performance, and compressing blade-casing clearance has become one of the main ways to improve turbomachinery efficiency. Rub-impact faults occur frequently with clearance decreasing. A high-speed rotor-support-casing test rig was set up, and the mechanism tests of light and heavy rub-impact were carried out. A finite element model of the test rig was established, and the calculation results were in good agreement with the experimental results under both kinds of rub-impact conditions. Based on the actual blade-casing structure model, the effects of the major physical p

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Sheard, A. G. "Blade by Blade Tip Clearance Measurement." International Journal of Rotating Machinery 2011 (2011): 1–13. http://dx.doi.org/10.1155/2011/516128.

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This paper describes a capacitance-based tip clearance measurement system which engineers have used in the most demanding turbine test applications. The capacitance probe has survived extended use in a major European gas turbine manufacturer's high-temperature demonstrator unit, where it functioned reliably at a turbine entry temperature in excess of 1800 degrees Kelvin. This paper explores blade by blade tip clearance measurement techniques and examines probe performance under laboratory conditions in support of high-temperature installations. The paper outlines the blade by blade tip clearan

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Dissertations / Theses on the topic ""turbine blade tip rub""

1

Langenbrunner, Nisrene A. "Understanding the Responses of a Metal and a CMCTurbine Blade during a Controlled Rub Event using a Segmented Shroud." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1366191740.

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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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Garza, Jared W. "Tip Rub Induced Blade Vibrations: Experimental and Computational Results." The Ohio State University, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=osu1391593189.

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Visagie, Willem Johannes. "Blade tip timing to determine turbine blade fatigue in high backpressure conditions." Diss., University of Pretoria, 2020. http://hdl.handle.net/2263/75831.

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This dissertation presents an approach to use blade tip timing measurements with finite element analysis to predict the fatigue life of a low pressure steam turbine last stage blade under high backpressure and low flow conditions. Material fatigue properties were determined through the extended universal material law for FV566 material, along with different temper scenarios. A finite element model of a blade with damping pins was developed, using the principle of cyclic symmetry for a perfectly tuned model. Pre-stress modal analysis was conducted, incorporating damping via friction and plastic

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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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Jousselin, Olivier. "Development of blade tip timing techniques in turbo machinery." Thesis, University of Manchester, 2013. https://www.research.manchester.ac.uk/portal/en/theses/development-of-blade-tip-timing-techniques-in-turbo-machinery(da682144-7009-4cdc-8f52-ff7cd0cf1cf1).html.

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In the current gas turbine market, the traditional design-test-redesign loop is not a viable solution to deploy new products within short timeframes. Hence, to keep the amount of testing to an absolute minimum, theoretical simulation tools like Finite Element Modelling (FEM) have become a driving force in the design of blades to predict the dynamic behaviour of compressor and turbine assemblies in high-speed and unsteady flows. The predictions from these simulation tools need to be supported and validated by measurements. For the past five years, Rolls-Royce Blade Tip Timing (BTT) technology h

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Saleh, Zainab Jabbar. "An investigation into turbine blade tip leakage flows at high speeds." Thesis, Queen Mary, University of London, 2015. http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937.

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This investigation studies the leakage flows over the high pressure turbine blade tip at high speed flow conditions. There is an unavoidable gap between the un-shrouded blade tip and the engine casing in a turbine stage, where the pressure difference between the pressure and the suction surfaces of the blade gives rise to the development of leakage flows through this gap. These flows contribute to about one third of the aerodynamic losses in a turbine stage. In addition they expose the blade tip to a very high temperature and result in thermal damages which reduce the blade‟s operational life.

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Anto, Karu. "Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/76764.

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The present study focuses on local heat transfer characteristics on the tip and near-tip regions of a turbine blade with a flat tip, tested under transonic conditions in a stationary, 2-D linear cascade consisting of seven blades, the three center blades having a variable tip clearance gap. The effects of tip clearance and exit Mach number on heat transfer distribution were investigated on the tip surface using a transient infrared thermography technique. In addition, thin film gages were used to study similar effects on the near-tip regions at 94% based on engine blade span of the pressure an

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Couch, Eric L. "Measurements of Cooling Effectiveness Along the Tip of a Turbine Blade." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/76815.

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In a gas turbine engine, turbine blades are exposed to temperatures above their melting point. Film-cooling and internal cooling techniques can prolong blade life and allow for higher engine temperatures. This study examines a novel cooling technique called a microcircuit, which combines internal convection and pressure side injection on a turbine blade tip. Holes on the tip called dirt purge holes expel dirt from the blade, so other holes are not clogged. Wind tunnel tests are used to observe how effectively dirt purge and microcircuit designs cool the tip. Tip gap size and blowing ratio are

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Mischo, Bob. "Axial turbine rotor aero-thermal blade tip performance improvement through flow control /." Zürich : ETH, 2008. http://e-collection.ethbib.ethz.ch/show?type=diss&nr=17813.

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Books on the topic ""turbine blade tip rub""

1

A, Davis Gary. Blade tip rubbing stress prediction: Final report. Rockwell International, Rocketdyne Division, 1991.

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Ameri, A. A. Analysis of gas turbine rotor blade tip and shroud heat transfer. National Aeronautics and Space Administration, 1996.

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Ameri, A. A. Analysis of gas turbine rotor blade tip and shroud heat transfer. National Aeronautics and Space Administration, 1998.

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4

Martinez-Sanchez, Manuel. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Massachusetts Institute of Technology, 1985.

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Martinez-Sanchez, Manuel. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Massachusetts Institute of Technology, 1985.

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Yamamoto, Atsumasa. Mechanisms of endwall/leakage flows and the associated losses in a linear turbine rotor cascade with blade tip-clearance. National Aerospace Laboratory, 1988.

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Kypuros, Javier A. A reduced model for prediction of thermal and rotational effects on turbine tip clearance. National Aeronautics and Space Administration, Glenn Research Center, 2003.

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Martinez-Sanchez, Manuel. Phase III report on contract number NAS8-35018 entitled Turbine blade tip and seal clearance excitation forces. National Aeronautics and Space Administration, 1992.

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Lattime, Scott B. Turbine engine clearance control systems: Current practices and future directions. National Aeronautics and Space Administration, Glenn Research Center, 2002.

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T, Arts, and Von Karman Institute for Fluid Dynamics., eds. Turbine blade tip design and tip clearance treatment: January 19-23, 2003. Von Karman Institute for Fluid Dynamics, 2004.

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Book chapters on the topic ""turbine blade tip rub""

1

Bunker, Ronald S. "Blade Tip Aerodynamics and Heat Transfer." In Turbine Aerodynamics, Heat Transfer, Materials, and Mechanics. American Institute of Aeronautics and Astronautics, Inc., 2014. http://dx.doi.org/10.2514/5.9781624102660.0351.0388.

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2

Sarath, R. S., R. Ajith Kumar, B. V. S. S. S. Prasad, and A. R. Srikrishnan. "Numerical Analysis of Effects of Turbine Blade Tip Shape on Secondary Losses." In Fluid Mechanics and Fluid Power – Contemporary Research. Springer India, 2016. http://dx.doi.org/10.1007/978-81-322-2743-4_82.

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3

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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Li, Jun, Xin Yan, Qiang Lv, Yonghui Xie, and Zhenping Feng. "The Effect of the Shrouded Rotor Blade Tip Leakage Flow on the Aerodynamic Performance of a One and Half Turbine Stage." In Challenges of Power Engineering and Environment. Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-76694-0_50.

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Xie, G., and B. Sunden. "Heat Transfer Enhancement of a Gas Turbine Blade-Tip Wall." In Emerging Topics in Heat Transfer. WIT Press, 2013. http://dx.doi.org/10.2495/978-1-84564-818-3/003.

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Ben Amira, Bilel, Mariem Ammar, Ahmad Kaffel, Zied Driss, and Mohamed Salah Abid. "The Effects of Curved Blade Turbine on the Hydrodynamic Structure of a Stirred Tank." In Vortex Dynamics Theories and Applications. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.92394.

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This work is aimed at studying the hydrodynamic structure in a cylindrical stirred vessel equipped with an eight-curved blade turbine. Flow fields were measured by two-dimensional particle image velocimetry (PIV) to evaluate the effect of the curved blade turbine. Velocity field, axial and radial velocity distribution, root mean square (rms) of the velocity fluctuations, vorticity, and turbulent kinetic energy were presented. Therefore, two recirculation loops were formed close to the free surface and in the bottom of the tank. Moreover, the highest value area of the vorticity is localized in the upper region of the tank which follows the same direction of the first circulation loop. The turbulent kinetic energy is maximum at the blade tip following the trailing vortices.

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Jayabalan, Jagan, Dalkilic Yildirim, Dookie Kim, and Pijush Samui. "Design Optimization of a Wind Turbine Using Artificial Intelligence." In Mathematical Concepts and Applications in Mechanical Engineering and Mechatronics. IGI Global, 2017. http://dx.doi.org/10.4018/978-1-5225-1639-2.ch003.

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This chapter examines the capability of Support Vector Machine (SVM), Relevance Vector Machine (RVM) and Genetic Programming (GP) for the optimal design of wind turbine. The excellent design has been influenced by various factors, such as profile of the blade, number of blades, power factor and tip speed ratio. The key to design a wind turbine is to Assessing the optimal tip speed ratio (TSR) is the key for designing the wind turbine. This chapter handles the Artificial Intelligence techniques in predicting the optimal TSR and the power factor based on the parameters engaged for NACA 4415 and LS-1 profile types with 3 and 4 blades. The organized machine learning framework is anticipated to be lucrative than the traditional way in foretelling the TSR and power factor. The machine learning models are then compared with the existing Neural Network model and the pros and cons of the various models are inferred from the results.

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Brahimi, Tayeb, and Ion Paraschivoiu. "Aerodynamic Analysis and Performance Prediction of VAWT and HAWT Using CARDAAV and Qblade Computer Codes." In Entropy and Exergy in Renewable Energy [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.96343.

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Wind energy researchers have recently invited the scientific community to tackle three significant wind energy challenges to transform wind power into one of the more substantial, low-cost energy sources. The first challenge is to understand the physics behind wind energy resources better. The second challenge is to study and investigate the aerodynamics, structural, and dynamics of large-scale wind turbine machines. The third challenge is to enhance grid integration, network stability, and optimization. This chapter book attempts to tackle the second challenge by detailing the physics and mathematical modeling of wind turbine aerodynamic loads and the performance of horizontal and vertical axis wind turbines (HAWT & VAWT). This work underlines success in the development of the aerodynamic codes CARDAAV and Qbalde, with a focus on Blade Element Method (BEM) for studying the aerodynamic of wind turbines rotor blades, calculating the induced velocity fields, the aerodynamic normal and tangential forces, and the generated power as a function of a tip speed ration including dynamic stall and atmospheric turbulence. The codes have been successfully applied in HAWT and VAWT machines, and results show good agreement compared to experimental data. The strength of the BEM modeling lies in its simplicity and ability to include secondary effects and dynamic stall phenomena and require less computer time than vortex or CFD models. More work is now needed for the simulation of wind farms, the influence of the wake, the atmospheric wind flow, the structure and dynamics of large-scale machines, and the enhancement of energy capture, control, stability, optimization, and reliability.

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Conference papers on the topic ""turbine blade tip rub""

1

Yan, Xin, Lijie Lei, Jun Li, and Zhenping Feng. "Effect of Bending and Mushrooming Damages on Heat Transfer Characteristic in Labyrinth Seals." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2012.

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Using conjugate heat transfer calculations, the heat transfer in straight-through labyrinth seals with and without rub damages (bending and mushrooming damages) were numerically investigated. Firstly, the numerical methods were carefully validated on the basis of obtained experimental data. At two different sealing clearances and a range of Reynolds numbers, Nu distributions on the seal rotor and stator surfaces for the original design cases were numerically computed and compared to the experimental data. The temperature fields in the fluid and inside the solid domains were obtained to account

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2

Glezer, B. "Turbine Blade Tip Clearance Improvement." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-164.

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A recently developed non-traditional design concept addressing turbine blade tip clearance reduction to provide long-term engine performance improvement and stability is presented. The concept is based on the direct attachment of the diaphragm, which supports Stage 1 integral nozzle and tips shroud segments, to the bearing housing, thus providing a close thermal link between the rotor and the stator. Transient thermal matching between the rotating and stationary structures was based on analytical prediction. Results of the complex turbine hot section study including cooling flow, thermal, stre

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Scrinzi, Erica, Iacopo Giovannetti, Nuo Sheng, and Luc Leblanc. "Development of New Abradable/Abrasive Sealing Systems for Clearance Control in Gas Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2065.

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Abradable/abrasive sealing systems are currently used in gas turbines to reduce the blade tip gas leakage and consequently improve the turbine efficiency. The coatings selection is directly related to the section in which they are used. Seal systems for hot gas paths are primarily required to withstand high temperature. The abradable coating should be easily removed by the tip blade without causing significant blade wear, whereas the blades should have sufficient cutting capabilities. Durability properties, such as erosion resistance, are also required. Owing to their temperature capabilities,

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Padova, Corso, Michael G. Dunn, Jeffery Barton, Kevin Turner, Alan Turner, and Darin DiTommaso. "Casing Treatment and Blade Tip Configuration Effects on Controlled Gas Turbine Blade Tip/Shroud Rubs at Engine Conditions." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50112.

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Experimental results obtained for an Inconel compressor blade rubbing bare-steel and treated casings at engine speed are described. Since 2002 a number of experiments were conducted to generate a broad database for tip rubs, the Rotor-Blade Rub Database (RBR database) obtained using the unique experimental facility at the OSU Gas Turbine Laboratory. As of 2007, there are seven completed groups of measurements in the database. Among them a number of blade-tip geometries and casing surface treatments have been investigated. The purpose of this paper is to provide a detailed interpretation of thi

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Park, Jung Shin, Sang Hoon Lee, Jae Su Kwak, Won Suk Lee, and Jin Taek Chung. "Measurement of Blade Tip Heat Transfer and Leakage Flow in a Turbine Cascade With a Multi-Cavity Squealer Tip." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2072.

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Tip leakage flow induces high heat transfer to the blade tip and causes significant aerodynamic losses. In this paper, we propose a multi-cavity squealer tip with an additional rib in the squealer cavity. Our study investigated the effects of the rib location and shape on the blade tip heat transfer and the total pressure loss. Experiments were performed in a five-bladed linear cascade using a low speed wind tunnel. The blade chord, pitch, and span length were 126mm, 102.7mm, and 160mm, respectively. The Reynolds number, based on the blade chord and cascade exit velocity, was 2.44×105, and a t

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Padova, Corso, Michael Dunn, Jeffrey Barton, Kevin Turner, and Tod Steen. "Controlled Fan Blade Tip/Shroud Rubs at Engine Conditions." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45223.

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The purpose of this paper is to describe the new facility design and operation improvements, and to demonstrate utility by providing typical results obtained as part of a typical measurement program. Since 2002 a number of experiments have been conducted to generate a broad database for tip rubs using two unique experimental facilities at the Gas Turbine Laboratory of The Ohio State University. Development of an in-ground spin-pit facility specifically designed to investigate rub-in-systems for jet engine components using real hardware rotating at representative engine speeds was reported seve

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Langenbrunner, Nisrene, Matt Weaver, Michael G. Dunn, Corso Padova, and Jeffery Barton. "Dynamic Response of a Metal and a CMC Turbine Blade During a Controlled Rub Event Using a Segmented Shroud." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-27156.

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Ceramic Matrix Composites, CMCs, provide several benefits over metal blades including weight and increased temperature capability, and have the potential for increased engine performance by reduction of the cooling flow bled from the compressor and by allowing engines to run at higher turbine inlet temperatures. These CMC blades must be capable of surviving fatigue (high cycle and low cycle), creep, impact, and any tip rub events due to the engine missions or maneuvers that temporarily close blade tip/shroud clearances. As part of a co-operative research program between GE Aviation and the Ohi

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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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Williams, Robin J. "Simulation of Blade Casing Interaction Phenomena in Gas Turbines Resulting From Heavy Tip Rubs Using an Implicit Time Marching Method." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45495.

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Severe rubs between gas turbine blades and engine casings can in extreme cases result in damaging blade vibration levels and rapid loss of casing lining material. Even for more minor rubs, the wear in the lining material will result in increase tip gaps and a consequent loss in efficiency. Major rub events are extremely rare in practice, and there is seldom any useful diagnostic evidence of the root cause of the behaviour. Moreover, traditional analysis methods are not suitable for exploring the wide range of potential conditions under which an unstable vibration response might be initiated. A

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Nagy, Douglas, and Robert Tollett. "Durable Abrasive Tip Design for Single Crystal Turbine Blades." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14449.

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Abstract:

Abstract In order to create and maintain peak efficiency in turbine stages, it is useful to minimize hot air leakage over blade tips. For unshrouded blades, this means creating minimal clearance over the airfoil tip with rub-tolerate zero-gap materials systems. In this study, a refractory abrasive tip material was developed and applied to a plain turbine blade tip to work in conjunction with an abradable coating on the tip-shoe. Process development efforts resulted in abrasive material that could be as much as 2mm thick. Further, the abrasive media included imbedded grits that would remain in

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Reports on the topic ""turbine blade tip rub""

1

Bennet, Edward M. The Effect of Blade Lean on an Axial Turbine Stator Flow Having Various Hub Tip Ratios. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada408925.

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2

Schobeiri, Meinhard, and Je-Chin Han. Aerodynamics and Heat Transfer Studies of Parameters Specific to the IGCC-Requirements: Endwall Contouring, Leading Edge and Blade Tip Ejection under Rotating Turbine Conditions. Office of Scientific and Technical Information (OSTI), 2014. http://dx.doi.org/10.2172/1131331.

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