Relevant bibliographies by topics / Damage to the turbo

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

Academic literature on the topic 'Damage to the turbo'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 February 2022

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Journal articles on the topic "Damage to the turbo"

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Xu, Xiao-lei, and Zhi-wei Yu. "Investigation of damage features of a turbo-disk." Engineering Failure Analysis 16, no. 5 (July 2009): 1554–61. http://dx.doi.org/10.1016/j.engfailanal.2008.10.010.

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Martin, Lynn M., Ratnakar Tripathi, Praveen Balne, James Landreneau, Sabeeh Kamil, Suneel Gupta, Nathan P. Hesemann, et al. "Turbo Eye Drops Restore Sulfur Mustard-Induced Corneal Damage." Toxicology Letters 331 (October 2020): 19. http://dx.doi.org/10.1016/j.toxlet.2020.05.071.

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Chen, Dongchao, Yuhao Zhang, and Yujiong Gu. "Online Evaluation of Turbo-Generator Shaft Fatigue Damage Caused by Subsynchronous Oscillation." IEEE Access 8 (2020): 55342–53. http://dx.doi.org/10.1109/access.2020.2981509.

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Gu, Yu Jiong, and Tie Zheng Jin. "Analysis on Torsional Fatigue Life of Turbo-Generator Shafts." Key Engineering Materials 467-469 (February 2011): 1858–63. http://dx.doi.org/10.4028/www.scientific.net/kem.467-469.1858.

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Both low-cycle fatigue and high-cycle fatigue exist during torsional vibrations, but the impact of high-cycle fatigue has rarely been considered. In this paper, a torsional fatigue life analyzing method used for torsional vibration of turbo-generator shafts has been developed based on Manson-Coffin equation and high-cycle fatigue theory. The method has been used to estimate the torsional fatigue life in the most dangerous section of the shafts in a power plant. The cumulative torsional fatigue damage under two-phase short circuit simulation has been predicted.
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Zhang, Rong Pei. "Vibration Characteristics and Damage of Turbine Generator Shaft Rubbing." Applied Mechanics and Materials 697 (November 2014): 210–13. http://dx.doi.org/10.4028/www.scientific.net/amm.697.210.

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An abnormal journal vibration occurred when a 660MW turbo generator unit was in daily operation. It was identified that rubbing vibration had taken place based on the behavior of the journal vibration and the temperature change of lubricating oil. The rubbing was located inside the bearing box between the HIP rotor and the LP rotor. However, no elimination measures had been taken in time because the damage caused by rubbing was underestimated. Few months later a full inspection revealed that the LP rotor shaft had been worn out with a 70mm wide and 28mm deep groove, which greatly weakened the strength of the LP rotor. The analysis presented here may help in diagnosing and understanding rubbing-vibration-related problems in similar situations.
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Kreischer, Christian. "Modern methods to monitor end winding vibrations in turbo-generators." COMPEL - The international journal for computation and mathematics in electrical and electronic engineering 38, no. 4 (July 1, 2019): 1214–23. http://dx.doi.org/10.1108/compel-10-2018-0403.

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Purpose Problems caused by end winding vibrations in power plant generators have become increasingly evident in recent years and reveal a need for monitoring and diagnostic systems. An increasing number of operational outages are caused by failures of the winding insulation or the conductor itself due to end winding vibrations. Meanwhile, it is clear that the condition of the end winding must be continuously monitored during operation to detect ineffective end winding support in time and to plan the repair. Design/methodology/approach In this paper, the complex and nonlinear excitation mechanisms in large machines are presented and modern methods for vibration monitoring are described. Through a consistent use of vibration monitoring in the end winding area as well as the vibration diagnosis done by experts, damage mechanisms can be detected at an early stage, repair measures can be planned and serious damage owing to a weakened main insulation can be avoided. Findings By combining modal analysis and trend monitoring in relation to the learned vibration behaviour, the end winding condition can be assessed in a differentiated manner and changes in the end winding structure can be detected early. Originality/value Finally, an assessment for a two-pole, air-cooled turbo generator is proposed.
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Gan, Hui, Kun Yu Yang, and Xiao Liang Yang. "Analysis of Structure Characteristics and Improvement of Turbo-Supercharger Bearing." Applied Mechanics and Materials 496-500 (January 2014): 707–10. http://dx.doi.org/10.4028/www.scientific.net/amm.496-500.707.

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The reliability of the gas turbo-supercharger can be affected by the faults such as the cauterization of the floating bearing of the supercharger, the carbonization of the rotor and getting stuck, the deformation of the blade and heat cracking of the nozzle ring. The design scheme is proposed by using friction bearing taking the place of the floating bearing, because the main reason of the cauterization of the bearing is the increase of the inside clearance of the floating sleeve, which is testified by the actual rpm measurement of the floating sleeve on the floating bearing and the adjustment test of the inside and outside clearances of the bearing. The experimental study on the structural characteristics of turbocharger bearing effectively prevents turbo-supercharger floating bearing from being cauterized, solves the problem of thermal fatigue damage, and improves turbocharger reliability.
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Dziendzikowski, Michal, Krzysztof Dragan, Artur Kurnyta, Sylwester Klysz, and Andrzej Leski. "Health Monitoring of the Aircraft Structure during a Full Scale Fatigue Test with Use of an Active Piezoelectric Sensor Network." Solid State Phenomena 220-221 (January 2015): 328–32. http://dx.doi.org/10.4028/www.scientific.net/ssp.220-221.328.

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The paper presents an approach to develop a system for fatigue crack growth monitoring and early damage detection in the PZL – 130 ORLIK TC II turbo-prop military trainer aircraft structure. The system functioning is based on elastic waves propagation excited in the structure by piezoelectric PZT transducers. In the paper, a built block approach for the system design, signal processing as well as damage detection is presented. Description of damage detection capabilities are delivered in the paper and some issues concerning the proposed signal processing methods and their application to crack growth estimation models are discussed. Selected preliminary results obtained during the Full Scale Fatigue Test thus far are also presented.
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Dragan, Krzysztof, Michal Dziendzikowski, and Tadeusz Uhl. "The Development of the Non-Parametric Classification Models for the Damage Monitoring on the Example of the ORLIK Aircraft Structure." Key Engineering Materials 518 (July 2012): 358–63. http://dx.doi.org/10.4028/www.scientific.net/kem.518.358.

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This paper presents approach for the damage growth monitoring and early damage detection in the PZL-130 ORLIK TC II turbo propeller military trainer based on the array of the PZT sensors which will be deployed in the structure of the aircraft. Special attention will be paid to the preliminary results of the statistical models which provide an automated tool to infer about the damage presence and its size. In particular the effectiveness of the selected signal characteristics will be assessed using dimensional reduction methods (PCA) and the so called averaged damage indices will be described. Verification of the several classification models based on the emerged damage indices will be presented using cross validation techniques. The preliminary results of the data collected from the subcomponents tests with the model description, as well as approach for the SHM system design will be delivered. The verification of the models results will be presented on the example of the aerospace structures.
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Xu, Xiao-lei, and Zhi-wei Yu. "Damage Features of Bolts Connecting Main-Shaft with Turbo-Disk Used in a Locomotive Turbocharger." Journal of Failure Analysis and Prevention 9, no. 4 (May 12, 2009): 380–84. http://dx.doi.org/10.1007/s11668-009-9258-6.

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Dissertations / Theses on the topic "Damage to the turbo"

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Vertaľ, Peter. "Provoz a údržba vozidel s přeplňovanými motory turbodmychadly." Master's thesis, Vysoké učení technické v Brně. Ústav soudního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-232496.

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The goal is to measure the temperature of the turbocharger after engine shutdown.Measurements wants to show the need to keep a car engine to cool after a heavier burden on the idle speed. It would also prevent possible disruptions turbocharger. The paper also deals with the problems, construction and basic principles of operation of the turbocharger
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Šedý, Jakub. "Turbo konvoluční a turbo blokové kódy." Master's thesis, Vysoké učení technické v Brně. Fakulta elektrotechniky a komunikačních technologií, 2011. http://www.nusl.cz/ntk/nusl-219287.

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The aim is to explain the Turbo convolutional and block turbo codes and decoding the secure message. The practical part focuses on the design of a demonstration program in Matlab. The work is divided into four parts. The first two deal with theoretical analysis of coding and decoding. The third section contains a description created a demonstration program that allows you to navigate the process of encoding and decoding. The fourth is devoted to simulation and performance of turbo codes.
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Fournier, Stéphan. "Turbo codes." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp04/mq22763.pdf.

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Yan, Yun. "Turbo codes." Ohio : Ohio University, 1999. http://www.ohiolink.edu/etd/view.cgi?ohiou1175200238.

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Raorane, Pooja Prakash. "Sampling Based Turbo and Turbo Concatenated Coded Noncoherent Modulation Schemes." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1279071861.

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Abbara, Mamdouh. "Turbo-codes quantiques." Phd thesis, Ecole Polytechnique X, 2013. http://pastel.archives-ouvertes.fr/pastel-00842327.

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L'idée des turbo-codes, construction très performante permettant l'encodage de l'information classique, ne pouvait jusqu'à présent pas être transposé au problème de l'encodage de l'information quantique. En effet, il subsistait des obstacles tout aussi théoriques que relevant de leur implémentation. A la version quantique connue de ces codes, on ne connaissait ni de résultat établissant une distance minimale infinie, propriété qui autorise de corriger un nombre arbitraire d'erreurs, ni de décodage itératif efficace, car les turbo-encodages quantiques, dits catastrophiques, propagent certaines erreurs lors d'un tel décodage et empêchent son bon fonctionnement. Cette thèse a permis de relever ces deux défis, en établissant des conditions théoriques pour qu'un turbo-code quantique ait une distance minimale infinie, et d'autre part, en exhibant une construction permettant au décodage itératif de bien fonctionner. Les simulations montrent alors que la classe de turbo-codes quantiques conçue est efficace pour transmettre de l'information quantique via un canal dépolarisant dont l'intensité de dépolarisation peut aller jusqu'à p = 0,145. Ces codes quantiques, de rendement constant, peuvent aussi bien être utilisés directement pour encoder de l'information quantique binaire, qu'être intégrés comme modules afin d'améliorer le fonctionnement d'autres codes tels que les LDPC quantiques.
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Barros, Jose da Silva. "Codigos turbo quaternarios." [s.n.], 2003. http://repositorio.unicamp.br/jspui/handle/REPOSIP/259772.

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Orientador: Renato Baldini Filho
Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Eletrica e Computação
Made available in DSpace on 2018-08-03T16:19:21Z (GMT). No. of bitstreams: 1 Barros_JosedaSilva_M.pdf: 832396 bytes, checksum: 7c6800b84777316838807b03162e680f (MD5) Previous issue date: 2003
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Xu, Lei. "OFDM turbo transceivers." Thesis, University of Southampton, 2008. https://eprints.soton.ac.uk/64480/.

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In this thesis a variety of different techniques designed for the sake of improving the attainable efficiency of wireless system are considered in the context of Orthogonal Frequency Division Multiplexing (OFDM). More explicitly, powerful turbo transceivers invoking Sphere Packing (SP) modulation are designed using EXtrinsic Information Transfer (EXIT) charts for both single-user and multi-user transmission. In order to provide an attractive suite of single-user OFDM transceivers, we contrive a SP-aided OFDM scheme for maximizing the achievable coding advantage. The corresponding capacity equation shows that the SP-OFDM scheme exhibits a higher capacity than its counterpart dispensing with SP. Furthermore, a carefully designed Sphere Packing symbol To Sub-Carrier Mapping (SPTSCM) scheme is contrived, which results in an improved Discrete Input Continuous Output Memoryless Channel (DCMC) capacity. This is achieved by reducing the correlation between the multiple OFDM sub-carriers conveying a specific SP symbol. In order to enhance the attainable BER performance of the SP-OFDM scheme, iterative detection is invoked for exchanging extrinsic information between the SP symbol-to-bit demapper and the channel decoder. In contrast to the classic SP signal construction, sophisticated SP schemes are designed with the aid of EXIT charts for the sake of improving the convergence behaviour of the iteratively detected schemes. Explicitly, an approximately 0.15bit/s/Hz DCMC capacity improvement is achieved and the proposed iterative detection aided SP-OFDM scheme becomes capable of performing within 2.1dB of the maximum achievable rate limit obtained using EXIT charts at BER = 10−4. Some of the proposed advances are then extended to a multi-user Space Division Multiple Access (SDMA) OFDM scheme. Novel turbo MUDs are designed and investigated in terms of their complexity, EXIT characteristics and BER performance. More explicitly, the linear turbo MUDs considered include the Complex-valued Minimum Mean Square Error (SIC-CMMSE) scheme, the Soft Interference Cancellation based Real-valued Minimum Mean Square Error (SIC-RMMSE) arrangement and the Soft Interference Cancellation based Minimum Bit-Error Rate (SIC-MBER) MUD schemes. The SIC-RMMSE is only applicable in the context of BPSK modulated schemes. A Reduced-complexity Minimum Bit-Error Rate (RMBER) is also designed for the sake of arriving at a complexity reduction by slightly compromising the attainable performance in comparison to the SIC-MBER MUD. Furthermore, a hybrid scheme was designed to eliminate the performance degradation imposed by the RMBER MUD. In contrast to above-mentioned linear schemes, Bayesian turbo MUD and the K-best iterative Sphere Decoder (SD) belong to the family of non-linear MUDs. Then a general complexityreduction technique was contrived in order to reduce the complexity imposed by the turbo MUDs, which was referred to as the A-priori-LLR-Threshold (ALT) aided MUD algorithm, which was introduced for the sake of striking an attractive trade-off between the attainable complexity-reduction and the performance degradation imposed. Finally, the novel framework of Transmit Domain Processing based Detectors (TDPD) was contrived for a generalized multi-access or multiplexing based channel model in order to circumvent the exponentially increasing complexity imposed by the Maximum Likelihood (ML) MUD as a function of both the number of antennas and the number of bits per symbol. Explicitly, the TDPD may be separated into three basic steps including the MUD’s Search Center (SC) calculation, detection candidate list generation and LLR output calculation. A range of different schemes were considered for each of the three steps, and the SIC-CMMSE SC aided hybrid K-best subset combination based iterative TDPD was capable of achieving a similar BER performance to the optimal ML detector at a significantly reduced-complexity.
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Mysore, Naveen. "Combined turbo coding and turbo equalization for wireless systems with antenna diversity." Thesis, McGill University, 2002. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=33983.

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Emerging wireless communication systems strive for very high data rates, increased coverage and good quality of service. To achieve these goals under harsh conditions on many wireless channels (e.g., due to fading, multipath interference, power constraints and bandwidth limitations), both antenna diversity schemes and channel coding should be utilized.
This thesis focuses on achieving reliable transmission over a class of multi-input multi-output Rayleigh faded channels at very low Signal-to-Noise Ratios (SNRs). The transmitter and receiver designs are based on turbo coding, multiple transmit/receive antennas and turbo equalization. Simulation studies were performed for systems with different coding rates, numbers of antennas and interleaving strategies. They show the ability to achieve small bit error rates (10-4--10-5) for negative values of SNR.
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Konuskan, Cagatay. "Turbo Equalization for HSPA." Thesis, Linköping University, Department of Electrical Engineering, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-54640.

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New high quality mobile telecommunication services are offered everyday and the demand for higher data rates is continuously increasing. To maximize the uplink throughput in HSPA when transmission is propagated through a dispersive channel causing self-interference, equalizers are used. One interesting solution, where the equalizer and decoder exchange information in an iterative way, for improving the equalizer performance is Turbo equalization.

In this thesis a literature survey has been performed on Turbo equalization methods and a chosen method has been implemented for the uplink HSPA standard to evaluate the performance in heavily dispersive channels. The selected algorithm has been adapted for multiple receiving antennas, oversampled processing and HARQ retransmissions. The results derived from the computer based link simulations show that the implemented algorithm provide a gain of approximately 0.5 dB when performing up to 7 Turbo equalization iterations. Gains up to 1 dB have been obtained by disabling power control, not using retransmission combining and utilizing a single receiver antenna. The algorithm has also been evaluated considering alternative dispersive channels, Log-MAP decoding, different code rates, number of Turbo equalization iterations and number of Turbo decoding iterations.

The simulation results do not motivate a real implementation of the chosen algorithm considering the increased computational complexity and small gain achieved in a full featured receiver system. Further studies are needed before concluding the HSPA uplink Turbo equalization approach.

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Books on the topic "Damage to the turbo"

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Turbo. Vigo: Edicións Xerais de Galicia, 1988.

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Arasu, A. Valan. Turbo machines. New Delhi: Vikas Publishing House, 2008.

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Luttwak, David. Turbo-capitalism. [S.l.]: Harper Business, 1998.

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Marateck, Samuel L. Turbo Pascal. New York: Wiley, 1991.

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Chirlian, Paul M. Turbo PROLOG. London: Merrill, 1988.

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Turbo Pascal. 5th ed. Reading, Mass: Addison-Wesley, 1998.

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Turbo drive. London: Scholastic, 2012.

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Turbo Pascal. Belmont, Calif: Wadsworth Pub. Co., 1992.

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International, Borland. Turbo assembler. Scotts Valley, CA: Borland, 1988.

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1958-, Mason Tom, and Copyright Paperback Collection (Library of Congress), eds. Going turbo. New York: Scholastic, 2001.

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Book chapters on the topic "Damage to the turbo"

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Wu, Zining. "Turbo Codes and Turbo Equalization." In Coding and Iterative Detection for Magnetic Recording Channels, 21–46. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/978-1-4615-4565-1_2.

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Cancellieri, Giovanni. "Turbo Codes." In Polynomial Theory of Error Correcting Codes, 473–502. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-01727-3_9.

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Besserer, Rolf. "Voith Turbo." In Voith Antriebstechnik, 278–89. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-31156-0_6.

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Besserer, Rolf. "Voith Turbo." In Voith Power Transmission, 279–89. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-68787-0_6.

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Aupperle, Martin. "Turbo Vision." In Turbo Pascal Version 6.0, 191–277. Wiesbaden: Vieweg+Teubner Verlag, 1991. http://dx.doi.org/10.1007/978-3-322-83043-2_9.

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Deergha Rao, K. "Turbo Codes." In Channel Coding Techniques for Wireless Communications, 161–207. New Delhi: Springer India, 2015. http://dx.doi.org/10.1007/978-81-322-2292-7_6.

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Regalia, Philip A. "Turbo Equalization." In Adaptive Signal Processing, 143–210. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2010. http://dx.doi.org/10.1002/9780470575758.ch3.

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Giulietti, Alexandre, Bruno Bougard, and Liesbet Van der Perre. "Turbo Codes." In Turbo Codes, 1–28. Boston, MA: Springer US, 2004. http://dx.doi.org/10.1007/978-1-4615-0477-1_1.

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Schneider, Andreas. "Turbo-Marketing." In Speed-Management, 125–30. Wiesbaden: Gabler Verlag, 1992. http://dx.doi.org/10.1007/978-3-322-94404-7_10.

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Mittelbach, Henning. "TURBO Pascal." In TURBO-PASCAL in Beispielen, 257–74. Wiesbaden: Vieweg+Teubner Verlag, 1997. http://dx.doi.org/10.1007/978-3-322-87185-5_15.

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Conference papers on the topic "Damage to the turbo"

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Stewart, Calvin M., and Ali P. Gordon. "Anisotropic Creep Damage and Elastic Damage of Notched Directionally Solidified Materials." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-46476.

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Drives to improve gas turbines efficiency have lead to an increase in firing temperatures. This increase in exhaust temperature has a negative impact upon turbine blade life. Both engineers and material scientists have produced methods to improve turbine blade life under these conditions. Cooling holes have become commonplace and use relatively cool gas to create a lower temperature barrier around a turbine blade. These cooling holes creating internal and external surfaces; a common sight of crack initiation. Directionally-solidified (DS) turbine blades have also become commonplace. These turbine blades exhibit a transversely-isotropic grain structure that improves creep strength in a desired direction. To model a component under such conditions, anisotropic constitutive models are required. In this paper, an anisotropic tertiary creep damage constitutive model for transversely-isotropic materials is given. The influence of creep-damage on general linear elasticity (elastic damage) is described by a modified Hooke’s compliance tensor. Finite element simulations of a V-notched tensile specimen are conducted to replicate a crack initiation site. A discussion on stress triaxiality, stress redistribution, and damage distribution due to anisotropy is provided.
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Duo´, Pierangelo, Christian Pianka, Andrej Golowin, Matthias Fueller, Roger Schaefer, and Ulf Bernhardt. "Simulated Foreign Object Damage on Blade Aerofoils: Real Damage Investigation." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50371.

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During operating service, gas turbine aero-engines can ingest small hard particles which typically produce damage to the aerofoils. If the damage found is a tear or a perforation at the leading edge, it is known as a Foreign Object Damage or FOD and this leads to a reduction of the subsequent High-Cycle-Fatigue (HCF) strength. The objective of research work in this area is to assess the effect of FOD on the residual fatigue strength of compressor blades and to provide predictive tools for engineering judgment. The methodology followed is normally to carry out experimental simulation of FOD, followed by fatigue tests to assess subsequent performance. To date, research related to fatigue following FOD events has concentrated on HCF loading and the impact geometry is frequently that of a sphere against a flat surface or the edge of a blade-like specimen. Both of these aspects do not correspond to the worst cases of real FOD. Here it is intended to investigate the effect of a V-notch geometry, which is more representative of severe FOD found in service. Alongside this, numerical models can be used to simulate the damage and to evaluate the residual stress field. In addition analytical model are used to predict the residual fatigue strength. The current work explains the development of a new rig impact test and discusses the improvements necessary to obtain a sufficient repeatability of the impacts. From the experience gained with a gas gun, an alternative method using a pistol and a barrel, capable of achieving the necessary velocity of simulated FOD, was developed. The applied velocity was in the range of 250m/s to 300m/s and a technique to describe the impact is here discussed. Furthermore the introduction of a high speed camera has allowed to have a complete description of the impact scene and to better understand the impact. The impacted blades were measured and HCF tested. As a result, this has produced a large scatter in the residual fatigue strength. The current method to describe a notch using a 2D approach, which was applied to several geometries of notches, is here critically reviewed. The proposed method would incorporate a more sophisticated method, which reconstruct the real geometry using optical measurement. This latter measurement can fully describe the 3D geometry, showing particularly zones inside the notch where compressive residual might appears. Tears and shear of the material can also be described by applying this technique. The findings are compared with the residual HCF strength and the results are compared to special cases of HCF to justify the results out of theoretical prediction.
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Scaletta, Brent, and Richard Green. "Critical Location Identification for Multi-Mechanistic Damage Modes Using Damage Interaction Charts." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14678.

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Abstract Damage in gas turbine engines can accumulate from multiple damage mechanisms including creep, fatigue, and oxidation. Each damage mechanism is influenced by various parameters which typically occur during different portions of engine operation. For instance, fatigue is influenced by large stress/strain ranges that occur during startup and shutdown transient conditions while creep is affected by sustained stress and temperature at dwell conditions. In some cases, the maximum damage location for one mechanism could experience negligible contribution in damage from any other mechanism, but in most cases, there is some degree of influence from two or three mechanisms. In those instances, damage will accumulate at various rates during separate portions of operation under different damage mechanisms. Since some applications require engines to dwell for long periods of time while other applications favor more frequent cycling, every engine will accumulate damage differently at each location. Therefore, it is difficult to estimate which location is critical to durability, rendering it necessary to capture all possible critical locations so that damage can be estimated for each application. This paper suggests a method by which to visualize and select critical locations based on all possible customer use scenarios. Once critical locations are identified, a Reduced Order Model (ROM) can be generated for each point of interest and damage can be estimated and monitored using data collection. Damage mechanisms can be combined if micromechanistic affects are additive, the material response compounds, or the material properties evolve with time. Examples of each case are demonstrated. In addition, the visual representation of damage interaction allows for uncertainty to be visualized and implemented to rank location criticality.
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Asundi, Anand. "Fiber Optic Sensors for Damage Detection in Composite Materials." In ASME 1997 Turbo Asia Conference. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-aa-067.

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An absence of proper design rules has limited the application of composite materials to specific areas. However, within these application areas there is still a need to regular monitor the component resulting in significant downtime and loss of revenue. To overcome this it is proposed to have an on-line monitoring system capable of global checking of the component. Fiber optic polarimetric sensors are chosen in this study to globally characterize the health of a component. Polarimetric sensors have better sensitivity than intensity sensors and at the same time are more rugged than interferometric sensors. In this study, the effect of debonds and fiber breakages are investigated in composite bend specimens.
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Nikhamkin, Mickhail S., Leonid V. Voronov, and Irina V. Semenova. "Effect of Blade Geometry and Foreign Object Kinetic Energy on Blades Damage." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-22425.

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One of the main reasons of engine failure is foreign object damage (FOD) of compressor blades. Engine manufactures are constantly searching for blade endurance increasing methods. The problem solution requires investigation in the field of the structural factor effects on the blade damageability. The paper describes numerical analysis method of the damage process. Based on “the typical damage case” concept, this method can simulate typical blade damages: dents, tears, notches. The numerical analysis is performed by the finite element method (FEM). Material behavior is described with an elastic-plastic strain rate dependent model. Blade damage numerical model is thoroughly verified by the results of special experiments. To implement the experimental modeling, actual blades were damaged, a special experimental setup based on a pneumatic gun being used. The foreign object kinematic parameters before and after the impact, a blade leading edge displacements and residual deformation fields registered in the experiment are used as verification criteria for the numerical model. The blade leading edge thickness and a foreign object energy effect on the blade damageability is investigated. The research showed there are some foreign object kinetic energy critical values at which the damage mechanism and type are changed.
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Nikhamkin, Mickhail S., Leonid V. Voronov, and Irina V. Semenova. "Foreign Object Damage and Fatigue Strength Loss in Compressor Blades." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51493.

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Foreign object damage (FOD) is always an all-important problem of gas turbine engines safety, reliability and operating costs. This paper describes experimental and numerical prediction investigations of FOD to compressor blades of gas turbine engine. Experimental modeling of FOD processes was done using a special plant on the base of a pneumatic gun. Real steel blades of a high-pressure compressor were impacted with spherical steel projectiles at the velocity about 200 m/s. Typical in-service damages as well as round dents, tears and bends were reproduced in the experiment. Numerical prediction analyses of the damage process were fulfilled by finite element method (FEM). Material behavior is described with elastic-plastic strain rate dependent model. We find the form and sizes of the calculated damages to be in good agreement with the experimental findings. Furthermore, the experimental and computational procedure for estimation of fatigue strength loss of damaged blades is proposed. It is based on study of stress concentration in damages. Stress concentration factor for different concentrator shapes was calculated using 3-D finite element analyses and refined via a stress concentration sensitivity factor. Stress concentration sensitivity factor was experimentally defined through fatigue tests of real blades with V-shape notches at leading edge. This technique supposes minimum laborious fatigue tests. Experimentally confirmed numerical methodology and model may be used for prediction study of FOD and fatigue strength loss of gas turbine engine blades.
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Scheibel, John R., Robert P. Dewey, Jay Richardson, Huawei Shi, and Swami Swaminathan. "Managing Compressor Rotor Rim Fatigue Damage." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63674.

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Described within this paper are the results derived from an investigation into the root cause of cracks which are prematurely forming within the aft end rotor rim attachments of large combustion turbine compressors. The overall objective for this program was to use these results to develop a means for projecting the remaining service life of similarly affected rotors based on non-destructive measurements which identified the degree of fatigue damage sustained in the critical disc rim fillets. Projected rotor retirement was identified by systematically calculating the change in stress intensity for a crack as it propagated from a corner of the attachment fillet through the disc rim. Risk of catastrophic failure was identified when the stress intensity along the front of a given crack size and depth exceeded the fracture toughness of the rotor material, risking failure. Estimates of both crack initiation and propagation relied on properties derived from fatigue tests of specimens obtained from a retired rotor and stress results from a transient thermal analysis of the stages. When compared, projections of crack growth correlated well against field measurements of damaged rims.
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Li, Yanling, and Abdulnaser Sayma. "Effects of Blade Damage on the Performance of a Transonic Axial Compressor Rotor." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68324.

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Gas turbine axial compressor blades may encounter damage during service for various reasons. Debris from casing or foreign objects may impact blades causing damage near the rotor’s tip. This may result in deterioration of performance and reduction in the surge margin. Ability to assess the effect of damaged blades on the compressor performance and stability is important at both the design stage and in service. The damage to compressor blades breaks the cyclic symmetry of the compressor assembly. Thus computations have to be performed using the whole annulus. Moreover, if rotating stall or surge occurs, the downstream boundary conditions are not known and simulations become difficult. This paper presents an unsteady CFD analysis of compressor performance with tip curl damage. Tip curl damage typically occurs when rotor blades hit a loose casing liner. The computations were performed up to the stall boundary, predicting rotating stall patterns. The aim is to assess the effect of blade damage on stall margin and provide better understanding of the flow behaviour during rotating stall. Computations for the undamaged rotor are also performed for comparison. A transonic axial compressor rotor is used for the time-accurate numerical unsteady flow simulations, with a variable choked nozzle downstream simulating an experimental throttle. One damaged blade was introduced in the rotor assembly and computations were performed at 60% of the design rotational speed. It was found that there is no significant effect on the compressor stall margin due to one damaged blade despite the differences in rotating stall patterns between the undamaged and damaged assemblies.
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Rehman, A. U., J. A. Rongong, and K. Worden. "Detection of Damage in Repeating Structures." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23351.

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Repeating structures in the form of multiple-bladed rotors are used widely in turbomachinery. Damage to blades can have significant consequences but can be difficult to identify in normal operation. This paper introduces an approach for identifying small defects such as cracks in a repeating structure that may be applicable to the limited data obtainable from developing techniques such as blade tip-timing. In order to understand the key issues involved, this initial work involves a numerical study of a simple comb-like repeating structure rather than a bladed rotor. Changes to the system modeshapes and mode order arising from damage are related to the location and severity of damage. Damage, in the form of small, open cracks, is modelled using different techniques such as material removal, periodic reduction in modulus of elasticity of selected elements at the required location and mass modification. Damage indices based on differences in the Modal Assurance Criterion (MAC) that give a measure of the change in the modeshapes are introduced. MAC matrices are obtained using a reduced number of data points. The damage index is obtained from the Frobenius norm of MAC matrix subtracted from (1) the AutoMAC of reference model without crack and (2) the identity matrix. A clear correlation between the damage indices and crack depth / location is shown. In order to account for mistuning in real repeating structures, the performance when the assembly is subjected to inhomogeneous temperature distributions is also considered.
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Kolle, Jack J., and Tony Theimer. "Testing of a Fluid-Powered Turbo-Acoustic Source for Formation-Damage Remediation." In SPE International Symposium and Exhibition on Formation Damage Control. Society of Petroleum Engineers, 2010. http://dx.doi.org/10.2118/128050-ms.

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Reports on the topic "Damage to the turbo"

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Whitener, Dustin Heath, and John Fulton. Turbo FRMAC Cloud Solutions. Office of Scientific and Technical Information (OSTI), September 2018. http://dx.doi.org/10.2172/1471655.

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Augustine, David B. Analysis of Booster Turbo Pump Manifolds. Office of Scientific and Technical Information (OSTI), August 2012. http://dx.doi.org/10.2172/1480093.

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Fulton, John. Deposition Velocity Modeling for Turbo FRMAC. Office of Scientific and Technical Information (OSTI), July 2018. http://dx.doi.org/10.2172/1463228.

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Urbach, Herman B. Differential Forms of Euler's Turbo-Machinery Equation. Fort Belvoir, VA: Defense Technical Information Center, April 1989. http://dx.doi.org/10.21236/ada207279.

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Horazak, Dennis. Zero Emissions Coal Syngas Oxygen Turbo Machinery. Office of Scientific and Technical Information (OSTI), December 2010. http://dx.doi.org/10.2172/1051564.

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Ransom, Roger, and Richard Sutch. One Kind of Freedom: Reconsidered (and Turbo Charged). Cambridge, MA: National Bureau of Economic Research, September 2000. http://dx.doi.org/10.3386/h0129.

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Abraham, J. Optimizing the turbo-roto-compound (TRC) engine. Final report. Office of Scientific and Technical Information (OSTI), August 1994. http://dx.doi.org/10.2172/206549.

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Kilper, Daniel, and Keren Bergman. TURBO: Terabits/s Using Reconfigurable Bandwidth Optics (Final Report). Office of Scientific and Technical Information (OSTI), May 2020. http://dx.doi.org/10.2172/1618041.

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Heywood, John, Young Suk Jo, Raymond Lewis, Leslie Bromberg, and John Heywood. Hige Compression Ratio Turbo Gasoline Engine Operation Using Alcohol Enhancement. Office of Scientific and Technical Information (OSTI), January 2016. http://dx.doi.org/10.2172/1241492.

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Wang, Guan-Jhong, Chia-Jui Chiang, Yu-Hsuan Su, and Yong-Yuan Ku. CFD Modeling of a Turbo-Charged Common-Rail Diesel Engine. Warrendale, PA: SAE International, October 2013. http://dx.doi.org/10.4271/2013-32-9103.

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