Relevant bibliographies by topics / Axial turbomachine

Contents

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

Academic literature on the topic 'Axial turbomachine'

Author: Grafiati
Published: 28 May 2022
Last updated: 31 July 2025

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Journal articles on the topic "Axial turbomachine"

1

Repetckii, Oleg, and Van Vinh Nguyen. "DYNAMIC CHARACTERISTICS ANALYSIS OF BLADED DISK TURBOMACHINES BASED ON INTENTIONAL MISTUNING." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 62 (2020): 61–70. http://dx.doi.org/10.15593/2224-9982/2020.62.07.

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To increase technical level of energy turbomachine in modern turbomachinery, high reliability and durability of structures are required in the design, manufacture and operation of turbomachine. Any change geometry, mass, material properties of the bladed disk of turbomachine in the design is called mistuning parameters. With a small value of mistuning blades can significantly increase amplitude, displacement or stresses of the blades structures. So, analysis influence of the effect mistuning parameters on the dynamic characteristics in the field of turbomachine is an important and urgent task.
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Walker, G. J. "Transitional flow on axial turbomachine blading." AIAA Journal 27, no. 5 (1989): 595–602. http://dx.doi.org/10.2514/3.10150.

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Saren, V. E., N. M. Savin, S. A. Smirnov, V. G. Krupa, and V. A. Yudin. "Hydrodynamic interaction of axial turbomachine cascades." Journal of Engineering Mathematics 55, no. 1-4 (2006): 9–39. http://dx.doi.org/10.1007/s10665-005-9022-1.

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Repetckii, O. V., and V. V. Nguyen. "Effect of Intentional Mistuning on Dynamic Characteristics of a Energy Turbomachine Bladed Disk." Journal of Physics: Conference Series 2096, no. 1 (2021): 012012. http://dx.doi.org/10.1088/1742-6596/2096/1/012012.

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Abstract In this article the effect intentional mistuning of an axial turbomachine bladed disk has been analyzed in order to reduce forced response due to low-order engine excitation. The maximum value of forced response of turbomachine rotor’s blades with mistuning parameters is usually much more than the value of the tuned rotors. An increase level mistuning of this critical value actually leads to a decrease magnifications of the forced response. Thus, the actual work has been introducing some degree of intentional mistuning in the design to achieve these purposes. The effectiveness of inte
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Nikolaev, Vitaly S., Sergey A. Abalakin, and Igor V. Tishchenko. "Comparison of efficiency losses due to leaks for turbine units of aviation air conditioning systems with petal-type gas-dynamic bearings and ball bearings." Refrigeration Technology 111, no. 1 (2022): 13–20. http://dx.doi.org/10.17816/rf96964.

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BACKGROUND: Designers of turbomachines strive to increase the efficiency of expanding compressed gases by reducing all kinds of energy losses, particularly due to clearances between the impeller and the body elements of the turbomachine.
 AIM: This article aimed to evaluate a possible increase in efficiency with a decrease in the radial and axial clearance between the blades of a radial-axial impeller and the casing of a centrifugal expander in the designs of turbomachines with ball bearings and petal-type gas-dynamic bearings.
 MATERIALS AND METHODS: The radial and axial clearances
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Tauveron, Nicolas, Manuel Saez, Pascal Ferrand, and Francis Leboeuf. "Axial turbomachine modelling with a 1D axisymmetric approach." Nuclear Engineering and Design 237, no. 15-17 (2007): 1679–92. http://dx.doi.org/10.1016/j.nucengdes.2007.01.019.

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Fernández Oro, Jesús Manuel, Eduardo Blanco Marigorta, Katia María Argüelles Díaz, and Rafael Ballesteros-Tajadura. "Forced and unforced unsteadiness in an axial turbomachine." Experimental Thermal and Fluid Science 33, no. 3 (2009): 449–59. http://dx.doi.org/10.1016/j.expthermflusci.2008.10.012.

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Sharma, O. P., and T. L. Butler. "Predictions of Endwall Losses and Secondary Flows in Axial Flow Turbine Cascades." Journal of Turbomachinery 109, no. 2 (1987): 229–36. http://dx.doi.org/10.1115/1.3262089.

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This paper describes the development of a semi-empirical model for estimating end-wall losses. The model has been developed from improved understanding of complex endwall secondary flows, acquired through review of flow visualization and pressure loss data for axial flow turbomachine cascades. The flow visualization data together with detailed measurements of viscous flow development through cascades have permitted more realistic interpretation of the classical secondary flow theories for axial turbomachine cascades. The re-interpreted secondary flow theories together with integral boundary la
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Varney, Philip, and Itzhak Green. "Dynamic modeling of an eccentric face seal including coupled rotordynamics, face contact, and inertial maneuver loads." Proceedings of the Institution of Mechanical Engineers, Part J: Journal of Engineering Tribology 232, no. 6 (2017): 732–48. http://dx.doi.org/10.1177/1350650117727230.

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Mechanical face seals are constitutive components of turbomachines, which in turn can be constitutive to other systems (e.g. aircraft). Furthermore, the rotating element of a face seal is inextricably coupled to the turbomachine via a flexible mount, and the stationary seal element is coupled to the rotating seal element via the fluid film existing between the seal faces. Consequentially, understanding interactions between the seal and turbomachine is important for quantifying seal performance and improving its design. With few exceptions, previous works study the face seal dynamics independen
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Ghenaiet, A., S. C. Tan, and R. L. Elder. "Prediction of an axial turbomachine performance degradation due to sand ingestion." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 4 (2005): 273–87. http://dx.doi.org/10.1243/095765005x7592.

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Erosion of compressor blades due to operation in particulate environments is a serious problem for the manufacturers and users of industrial and aeronautical gas turbines, because of drastic degradations in performance, mostly through blunting of blade leading edges, reduction of chord and increase of tip clearance and surface roughness. This paper presents a numerical study to assess the effects of erosion by sand ingestion on blade geometry deterioration and the subsequent performance degradation. These computations were carried out for an axial turbomachine in steps; first, calculations of
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Dissertations / Theses on the topic "Axial turbomachine"

1

Hall, David Kenneth. "Performance limits of axial turbomachine stages." Thesis, Massachusetts Institute of Technology, 2011. http://hdl.handle.net/1721.1/63042.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2011.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (p. 111-114).<br>This thesis assesses the limits of stage efficiency for axial compressor and turbine stages. A stage model is developed, consisting of a specified geometry and a surface velocity distribution with turbulent boundary layers. The assumptions and parameterization of the stage geometry allow for calculation of the magnitude of various loss sources in terms of eight input parameters. By (1) considering onl
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Berger, Valérie. "Caractérisation expérimentale des phénomènes instationnaires dans un compresseur axial de turbomachine." Toulouse, ENSAE, 1987. http://www.theses.fr/1987ESAE0006.

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Les phénomènes instationnaires dans les compresseurs de turbomachine, (pompage, décollement tournant, sillage de roue mobile), ont été étudiés avec comme support expérimental des mesures réalisées sur compresseur H. P. Deux étages LARZAG spécialement instrumenté. Plusieurs théories caractérisant l'initiation et le type de phénomènes instationnaires en fonction du compresseur sont présentées (GREITZER, DAY et CUMPSTY, MOORE , FERRAND, societé BERTlN). La réalisation de mesures stationnaires a permis la mise en œuvre d'un programme de modélisation d'écoulement compressseur. Un code de calcul de
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Berger, Valérie. "Caractérisation expérimentale des phénomènes instationnaires dans un compresseur axial de turbomachine." Grenoble : ANRT, 1987. http://catalogue.bnf.fr/ark:/12148/cb37593744b.

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Wang, Juan. "Experimental study of two counter rotating axial flow fans." Thesis, Paris, ENSAM, 2014. http://www.theses.fr/2014ENAM0024/document.

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RESUME : Les machines axiales à rotors contrarotatifs subsoniques sont une bonne solution pour les industries où de fortes élévations de pressions et d'efficacités sont nécessaires sans augmenter le diamètre ou la vitesse de rotation des rotors. Néanmoins, le comportement des CRS et les paramètres impactant ses performances ne sont pas encore totalement compris. Cette thèse mène une investigation expérimentale sur la performance et les paramètres influents sur un étage contrarotatif. La technique de design et les méthodes de mesure sont repris sur une thèse précédente réalisée au laboratoire D
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Каплун, Ігор Петрович, Игорь Петрович Каплун, Ihor Petrovych Kaplun, Михайло Богданович Оприско, Михаил Богданович Опрыско та Mykhailo Bohdanovych Oprysko. "Огляд основних способів регулювання параметрів осьових турбомашин". Thesis, Сумський державний університет, 2016. http://essuir.sumdu.edu.ua/handle/123456789/45581.

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Осьові турбомашини (тут і далі маються на увазі насоси, вентилятори та низькошвидкісні компресори, швидкості газу яких достатньо малі, щоб знехтувати його стискуваністю) здавна привертають до себе увагу фахівців завдяки своїм унікальним якостям.
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Vézina, Gabriel. "Aérodynamique d'une turbomachine à architecture concentrique de type SRGT (Supersonic RIM-ROTOR gaz turbine)." Mémoire, Université de Sherbrooke, 2014. http://hdl.handle.net/11143/5419.

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Le groupe de recherche CAMUS de l'Université de Sherbrooke a conceptualisé et breveté en 2011 une nouvelle architecture de turbine à gaz nommé SRGT (Supersonic Rim-Rotor Gas Turbine). Aucune démonstration expérimentale n’a encore permis d’évaluer ses performances. Ce projet de maitrise consiste donc à l’analyse de la dynamique des gaz d’une turbomachine de type SRGT afin d’évaluer la possibilité de générer de la puissance nette positive en régime permanent. L’objectif de ce projet de recherche est de concevoir les composantes aérodynamiques d’une turbine à gaz SRGT en mode supersonique et de c
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Ji, Min. "Fully three-dimensional and viscous semi-inverse method for axial/radial turbomachine blade design." Related electronic resource: Current Research at SU : database of SU dissertations, recent titles available full text, 2008. http://wwwlib.umi.com/cr/syr/main.

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Fakher, El Abiari Salah Eddine. "Modélisation des régimes d'écoulements instationnaires rencontrés en turbomachine axiale." Ecully, Ecole centrale de Lyon, 1987. http://www.theses.fr/1987ECDL0007.

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Ge, Ning. "Contribution à l'étude du décollement tournant dans les ventilateurs axiaux par vélocimétrie Doppler à laser et visualisation." Valenciennes, 1993. https://ged.uphf.fr/nuxeo/site/esupversions/4e75b118-426c-4ae9-aa47-2cc24195edb4.

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Dans un ventilateur axial, le décollement tournant peut être caractérisé par des cellules à débit réduit, nul ou négatif qui se propagent dans le sens de la rotation du ventilateur à une vitesse angulaire constante. L'objectif de notre travail a consisté à utiliser les méthodes expérimentales telles que la vélocimétrie laser, le fil chaud et la technique de visualisation pour étudier l'apparition de ce phénomène. En général, les sondes perturbent l'écoulement. La mesure sans contact du fluide par vélocimétrie laser nous permet une approche plus fine du phénomène étudié. Des fils chauds simples
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Marteel, Sophie. "Etude aéroacoustique du spectre de raies d'un ventilateur axial en régime subsonique." Valenciennes, 1992. https://ged.uphf.fr/nuxeo/site/esupversions/16b3c69a-aa2a-48be-98a1-ac403fea8c7a.

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Ce travail consiste dans l’étude, pour un ventilateur axial, des phénomènes aérodynamiques susceptibles de générer des raies acoustiques à la fréquence de passages des pales et à ses harmoniques et les essais sont réalisés pour le point d’adaptation. Un modèle de prédiction, qui permet le calcul de la pression acoustique pour la fréquence de passage des pales et ses harmoniques, a été élaboré par Lowson. Il repose sur le rayonnement sonore des forces instationnaires en mouvement circulaire agissant sur les aubages dont l’amplitude, décomposable en série de Fourier, dépend de la valeur de la fo
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Books on the topic "Axial turbomachine"

1

Max, Platzer, Carta Franklin O, North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel., and North Atlantic Treaty Organization. Advisory Groupfor Aerospace research and Development. Structures and Materials Panel., eds. AGARD manual on aeroelasticity in axial-flow turbomachines. Volume 1: Unsteady turbomachinery aerodynamics. AGARD, 1987.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Blading design for axial turbomachines. AGARD, 1989.

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T, Fransson, Sieverding C. H. 1939-, and Von Karman Institute for Fluid Dynamics., eds. Aeroelasticity in axial flow turbomachines: May 3-7, 1999. von Karman Institute for Fluid Dynamics, 1999.

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Arasu, A. Valan. Turbo machines. Vikas Publishing House, 2008.

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1939-, Sieverding C. H., Hodson H. P, and Von Karman Institute for Fluid Dynamics., eds. Blade row interference effects in axial turbomachinery stages: February 9-12, 1998. Von Karman Institute for Fluid Dynamics, 1998.

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United States. National Aeronautics and Space Administration., ed. An interactive grid generation procedure for axial and radial flow turbomachinery. National Aeronautics and Space Administration, 1990.

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1945-, Sharma Om P., and United States. National Aeronautics and Space Administration., eds. Impact of periodic unsteadiness on performance and heat load in axial flow turbomachines. National Aeronautics and Space Administration, 1997.

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O, Carta F., and North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development., eds. AGARD manual on aeroelasticity in axial-flow turbomachines, vol.2. Structural dynamics and aeroelasticity. AGARD, 1988.

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S, Dhadwal Harbans, and NASA Glenn Research Center, eds. Simultaneous optical measurements of axial and tangential steady-state blade deflections. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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S, Dhadwal Harbans, and NASA Glenn Research Center, eds. Simultaneous optical measurements of axial and tangential steady-state blade deflections. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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Book chapters on the topic "Axial turbomachine"

1

Fransson, T. H., and J. M. Verdon. "Panel Discussion on Standard Configurations for Unsteady Flow Through Vibrating Axial-Flow Turbomachine-Cascades." In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers. Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_44.

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Dick, Erik. "Axial Compressors." In Fundamentals of Turbomachines. Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9627-9_13.

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Dick, Erik. "Axial Compressors." In Fundamentals of Turbomachines. Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-93578-8_13.

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Dick, Erik. "Axial and Radial Turbines for Gases." In Fundamentals of Turbomachines. Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9627-9_15.

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Dick, Erik. "Axial and Radial Turbines for Gases." In Fundamentals of Turbomachines. Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-93578-8_15.

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Sultanian, Bijay K. "Axial-Flow Gas Turbines." In Fluid Mechanics and Turbomachinery. CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-12.

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Sultanian, Bijay K. "Axial-Flow Pumps, Fans, and Compressors." In Fluid Mechanics and Turbomachinery. CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-10.

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Chauvin, Jacques. "Axial Flow Compressor Performance." In Thermodynamics and Fluid Mechanics of Turbomachinery. Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-5153-2_21.

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Sieverding, C. H. "Aerodynamic Development of Axial Turbomachinery Bladings." In Thermodynamics and Fluid Mechanics of Turbomachinery. Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-5153-2_15.

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Sieverding, C. H. "Axial Turbine Performance Prediction Methods." In Thermodynamics and Fluid Mechanics of Turbomachinery. Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-5153-2_22.

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Conference papers on the topic "Axial turbomachine"

1

WALKER, G. "Transitional flow on axial turbomachine blading." In 25th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-10.

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Shun, Kang, Liu Fengjun, and Wang Zhongqi. "A Method for Calculating Axial Turbomachine End Wall Turbulent Boundary Layers." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-15.

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Based on two families of relative stream-surface theory, the differential and integral equations of the endwall boundary layer in the S2 stream surface (hub to tip stream surface) have been established in the orthogonal curvilinear coordinate system in the present paper. By directly associating the blade force defects with the warping of S2 stream surface near the endwall, we have proposed a new method for predicting the endwall boundary layer. This method can be used to conduct the interactions of the end wall boundary layer with the S2 stream surface potentisl flow, in order to get the itera
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Sanders, A., and S. Fleeter. "Vane row indexing for passive vibration control of axial flow turbomachine rotors." In 31st Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-2656.

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Bruna, Dario, Carlo Cravero, Mark G. Turner, and Ali Merchant. "An Educational Software Suite for Teaching Design Strategies for Multistage Axial Flow Compressors." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27160.

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The T-AXI turbomachinery design system, an axisymmetric methodology recently developed with an educational purpose, has shown great capabilities in the redesign of existing axial flow gas turbine components. Different turbomachines, single or multistage configurations, have been already reproduced with excellent overall performance results: examples are the NASA/GE E3 HP compressor and LP turbine. In this paper the authors present a detailed analysis of the results of a “case-study” application of the code, as a complementary tool to be used during a turbomachinery design course. The NASA/GE E
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Goodisman, M. I., M. L. G. Oldfield, R. C. Kingcombe, T. V. Jones, R. W. Ainsworth, and A. J. Brooks. "An Axial Turbobrake." 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-001.

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The Axial Turbobrake (Patent applied for) is a novel turbomachine which can be used to absorb power generated by test turbines. Unlike a compressor there is no pressure recovery through the turbobrake. This simplifies the aerodynamic design and enables high stage loadings to be achieved. The blades used have high turning two dimensional profiles. This paper describes a single stage axial turbobrake, which is driven by the exhaust gas of the test turbine and is isolated from the turbine by a choked throat. In this configuration no fast acting controls are necessary as the turbobrake operates au
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Brzozowski, Daniel, Oguz Uzol, Yi-Chih Chow, Joseph Katz, and Charles Meneveau. "A Comparison of Unsteady RANS Simulations With PIV Data in an Axial Turbomachine." In ASME 2005 Fluids Engineering Division Summer Meeting. ASMEDC, 2005. http://dx.doi.org/10.1115/fedsm2005-77318.

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This paper presents a comparison of 2D unsteady Reynolds Averaged Navier-Stokes (RANS) simulations using two standard turbulence models, i.e. RNG k-ε and a Reynolds Stress Transport Model, with experimental data, obtained using two-dimensional Particle Image Velocimetry (PIV) measurements within an entire stage of an axial turbomachine. The computations are performed using the commercial flow solver FLUENT™. A sliding mesh interface between the rotor and stator domains is used. The PIV measurements are performed in a refractive-index-matched facility that provides unobstructed view, and cover
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Chen, Huang, Yuanchao Li, Subhra Shankha Koley, and Joseph Katz. "Effects of Axial Casing Grooves on the Structure of Turbulence in the Tip Region of an Axial Turbomachine Rotor." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15229.

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Abstract Challenges in predicting the turbulence in the tip region of turbomachines include anisotropy, inhomogeneity, and non-equilibrium conditions, resulting in poor correlations between the Reynold stresses and the corresponding mean strain rate components. The geometric complexity introduced by casing grooves exacerbates this problem. Taking advantage of a large database collected in the refractive index-matched liquid facility at JHU, this paper examines the evolution of turbulence in the tip region of an axial turbomachine with and without axial casing grooves, and for two flow rates. T
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Egorov, I. N. "Deterministic and Stochastic Optimization of a Variable Axial Flow Compressor." In ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-397.

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A procedure is proposed to determine geometrical parameters and control laws of rows of a variable multistage axial flow compressor (VMAC) which are optimum by a criterion of ensuring turbomachine high efficiency within a wide range of operating modes under the row control. It is demonstrated that in shaping a layout of a variable compressor, it is expedient to determine its row geometry on the basis of control efficiency assessment. The paper illustrates a possibility to increase turbomachine efficiency (up to 8%) through optimum monitoring of its rows when studying a compressor as a separate
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Sharma, O. P., and T. L. Butler. "Predictions of Endwall Losses and Secondary Flows in Axial Flow Turbine Cascades." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-228.

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The development of a semi-empirical model for estimating endwall losses is described in this paper. The model has been developed from improved understanding of complex endwall secondary flows, acquired through review of flow visualization and pressure loss data for axial flow turbomachine cascades. The flow visualization data together with detailed measurements of viscous flow development through cascades have permitted more realistic interpretation of the classical secondary flow theories for axial turbomachine cascades. The re-interpreted secondary flow theories together with integral bounda
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Fleeter, Sanford. "Real Forcing Functions for Turbomachine Forced Response Analysis." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-0642.

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Abstract Accurate design predictions of blade row HCF can not be made because important unsteady aerodynamic phenomena are not modeled in current aerodynamic analyses. Experimental results are examined to indicate the issues to be addressed in advanced HCF design analyses. The immediate industry need is advanced wake correlation models. Next, three dimensional vortical and potential forcing function components must be addressed. Also, the time-average wake may not be the only key variable for multistage turbomachines, with passage-to-passage variability important. Multiple harmonics are requir
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Reports on the topic "Axial turbomachine"

1

Katz, Joseph, and Charles Meneveau. Instrumentation to Support PIV and HPIV Measurements in an Axial Turbomachine Flow Visualization Facility. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada388848.

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Katz, Joseph, and Charles Meneveau. Instrumentation for 2D and 3D Holographic Particle Image Velocimetry in Axial Turbomachines. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada381937.

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