Relevant bibliographies by topics / Axial turbine stage

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

Academic literature on the topic 'Axial turbine stage'

Author: Grafiati
Published: 30 May 2022
Last updated: 31 May 2022

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Journal articles on the topic "Axial turbine stage"

1

Goodisman, M. I., M. L. G. Oldfield, R. C. Kingcombe, T. V. Jones, R. W. Ainsworth, and A. J. Brooks. "An Axial Turbobrake." Journal of Turbomachinery 114, no. 2 (1992): 419–25. http://dx.doi.org/10.1115/1.2929160.

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The “Axial Turbobrake” (patent applied for) is a novel turbomachine that 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
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Klimko, Marek, Pavel Žitek, and Richard Lenhard. "Measurement on Axial Reaction Turbine Stage." MATEC Web of Conferences 328 (2020): 03013. http://dx.doi.org/10.1051/matecconf/202032803013.

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This article describes a measuring methods and evaluating measured data on a single-stage axial turbine with reaction (~ 50 %). One turbine operating mode was selected, in which the traversing behind the nozzle and bucket with two 5-hole pneumatic probes took place. The results are distributions of flow angles, reactions, or losses distribution/efficiencies along the blades.
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Touil, Kaddour, and Adel Ghenaiet. "Blade stacking and clocking effects in two-stage high-pressure axial turbine." Aircraft Engineering and Aerospace Technology 91, no. 8 (2019): 1133–46. http://dx.doi.org/10.1108/aeat-03-2018-0110.

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Purpose The purpose of this paper is to characterize the blade–row interaction and investigate the effects of axial spacing and clocking in a two-stage high-pressure axial turbine. Design/methodology/approach Flow simulations were performed by means of Ansys-CFX code. First, the effects of blade–row stacking on the expansion performance were investigated by considering the stage interface. Second the axial spacing and the clocking positions between successive blade–rows were varied, the flow field considering the frozen interface was solved, and the flow interaction was assessed. Findings The
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Gregory, Brent A. "How Many Turbine Stages?" Mechanical Engineering 139, no. 05 (2017): 56–57. http://dx.doi.org/10.1115/1.2017-may-5.

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This article discusses various stages of turbines and the importance of having more stages in turbine design. The article also highlights reasons that determine the designer’s choice to select the number of turbine stages for a given design of gas turbine. The highest performance turbines are defined by lower work requirements and slower velocities in the gas path. The fundamental factors determining performance might be relegated to only two factors: demand on the turbine and axial velocity. Aircraft engine technologies drive new initiatives because of the need to increase firing temperature
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Koprowski, Arkadiusz, and Romuald Rządkowski. "Optimization of Curtis stage in 1 MW steam turbine." E3S Web of Conferences 137 (2019): 01039. http://dx.doi.org/10.1051/e3sconf/201913701039.

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When operating at 3000 rpm, small turbines do not require a gear box and the generator does not require complex electronic software. This paper analyses the various geometries of the Curtis stage, comprising two rotor and stator blades with and without an outlet, from the efficiency point of view. Presented are 3D steady viscous flows. The results were compared with the performance of an axial turbine.
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Agbadede, Roupa, Dennis Uwakwe, and Isaiah Allison. "Preliminary Re-design of an Axial Turbine in an Existing Engine to Meet the Increased Load Demand." European Journal of Engineering Research and Science 5, no. 11 (2020): 1360–64. http://dx.doi.org/10.24018/ejers.2020.5.11.2141.

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This work presents a preliminary design of an axial turbine section in an industrial gas turbine. The design was necessitated following the need to provide a gas turbine of a power output in the range of 48 to 60MW for a mini-city harbouring an oil rig, which was not possible with the old engine. The turbine section is designed to produce a power capable of driving the compressor as well as produce a useful power for electricity. Using proprietary gas turbine performance simulation software called TURBOMATCH and a computer program written in Microsoft Excel, a redesign of the axial turbine com
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Agbadede, Roupa, Dennis Uwakwe, and Isaiah Allison. "Preliminary Re-design of an Axial Turbine in an Existing Engine to Meet the Increased Load Demand." European Journal of Engineering and Technology Research 5, no. 11 (2020): 1360–64. http://dx.doi.org/10.24018/ejeng.2020.5.11.2141.

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This work presents a preliminary design of an axial turbine section in an industrial gas turbine. The design was necessitated following the need to provide a gas turbine of a power output in the range of 48 to 60MW for a mini-city harbouring an oil rig, which was not possible with the old engine. The turbine section is designed to produce a power capable of driving the compressor as well as produce a useful power for electricity. Using proprietary gas turbine performance simulation software called TURBOMATCH and a computer program written in Microsoft Excel, a redesign of the axial turbine com
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Salah, Salma I., Mahmoud A. Khader, Martin T. White, and Abdulnaser I. Sayma. "Mean-Line Design of a Supercritical CO2 Micro Axial Turbine." Applied Sciences 10, no. 15 (2020): 5069. http://dx.doi.org/10.3390/app10155069.

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Supercritical carbon dioxide (sCO2) power cycles are promising candidates for concentrated-solar power and waste-heat recovery applications, having advantages of compact turbomachinery and high cycle efficiencies at heat-source temperature in the range of 400 to 800 ∘C. However, for distributed-scale systems (0.1–1.0 MW) the choice of turbomachinery type is unclear. Radial turbines are known to be an effective machine for micro-scale applications. Alternatively, feasible single-stage axial turbine designs could be achieved allowing for better heat transfer control and improved bearing life. Th
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Němec, Martin, and Tomáš Jelínek. "Adaptable test rig for two-stage axial turbine." MATEC Web of Conferences 345 (2021): 00022. http://dx.doi.org/10.1051/matecconf/202134500022.

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This contribution describes a new test rig for a two-stage axial turbine built in the VZLÚ. The test rig has replaced an original facility used for a full stage aerodynamics investigation. The motivation for the design of the new test facility was the limitations of the original one. The design is briefly discussed, and then the first measurement results are presented. The first operation was performed with a turbine stage already measured in the original facility. This allows the comparison of the most important quantities.
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Jelínek, Tomáš, and Martin Němec. "Investigation of unsteady flow in axial turbine stage." EPJ Web of Conferences 25 (2012): 01035. http://dx.doi.org/10.1051/epjconf/20122501035.

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Dissertations / Theses on the topic "Axial turbine stage"

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Shannon, Kevin R. (Kevin Robert). "Loss mechanisms in a highly loaded transonic axial turbine stage." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/120440.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2018.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 129-130).<br>Flow in a one-and-a-half stage highly loaded transonic axial turbine representative of future generation turbine technology is assessed for its role in loss generation. Steady and unsteady two-dimensional and three-dimensional flow computations, complemented by simplistic control volume analyses as well as test data, provided results for establishing the quantitative level of loss from various
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Miller, Robert John. "An investigation into the unsteady blade interaction in one and a half stage axial flow turbine." Thesis, University of Oxford, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.299161.

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Stefanis, Vassilis. "Investigation of flow and heat transfer in stator well cavities of a two-stage axial turbine." Thesis, University of Sussex, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.444347.

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Dominik, Dávid. "Návrh aeroderivátu pro využití v kompresních stanicích." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417593.

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This thesis is concerned with the calculation of the power turbine. This turbine should be used in the automatic drive of the compressor used for compression of natural gas in compressor stations. Flight engine aeroderivate from the Rolls-Roye company, type RB211-22B, was used as gas generator. The main aim of the thesis is to summarize of the base atributes of the combustion turbines and aeroderivates. They are used for automatic engine, application a thermodynamic calculation of the power turbine, for reaction stage and basic strength calculations.
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Hauptmann, Thomas [Verfasser]. "Einfluss regenerationsbedingter Varianzen der Schaufelgeometrie auf erzwungene Schwingungen in einer mehrstufigen Turbine : The influence of regeneration-induced variances on forced response in a multi-stage axial turbine / Thomas Hauptmann." Hannover : Gottfried Wilhelm Leibniz Universität Hannover, 2020. http://d-nb.info/1216240930/34.

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Baker, Jonathan D. "Analysis of the sensitivity of multi-stage axial compressors to fouling at various stages." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Sep%5FBaker.pdf.

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Максюта, Дмитрий Игоревич. "Комбинированный метод аэродинамической оптимизации ступени осевой турбины". Thesis, НТУ "ХПИ", 2016. http://repository.kpi.kharkov.ua/handle/KhPI-Press/21648.

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Диссертация на соискание ученой степени кандидата технических наук по специальности 05.05.16 – турбомашины и турбоустановки. – Национальный технический университет "Харьковский политехнический институт", Харьков, 2016. Диссертация посвящена разработке комбинированного метода аэродинамической оптимизации ступени осевой турбины, который основываясь на поочередном решении одномерной и трехмерной задач, позволяет значительно повысить эффективность всей ступени при этом учитывая как характер течения рабочего тела в решетках, так и влияние на него протечек. На основании современной тенденций к испол
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Максюта, Дмитро Ігорович. "Комбінований метод аеродинамічної оптимізації ступеня осьової турбіни". Thesis, НТУ "ХПІ", 2016. http://repository.kpi.kharkov.ua/handle/KhPI-Press/21646.

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Дисертація присвячена розробці комбінованого методу аеродінамічної оптимізації ступеня осьової турбіни, який ґрунтуючись на почерговому вирішенні одновимірної та тривимірної задач, дозволяє значно підвищити ефективність всього ступеня враховуючи як характер течії робочого тіла в решітках, так і вплив на неї витоки. На підставі сучасної тенденцій до використання методів чисельної аеродинаміки (CFD) при оптимізації проточних частин осьових турбін і при цьому задіяючи якомога більшу кількість управляючих параметрів в оптимізаційному процесі, запропонований комбінований метод оптимізації. Запропон
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"Experimental Study of Main Gas Ingestion in a Subscale 1.5-stage Axial Flow Air Turbine." Master's thesis, 2015. http://hdl.handle.net/2286/R.I.36468.

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abstract: Gas turbine efficiency has improved over the years due to increases in compressor pressure ratio and turbine entry temperature (TET) of main combustion gas, made viable through advancements in material science and cooling techniques. Ingestion of main combustion gas into the turbine rotor-stator disk cavities can cause major damage to the gas turbine. To counter this ingestion, rim seals are installed at the periphery of turbine disks, and purge air extracted from the compressor discharge is supplied to the disk cavities. Optimum usage of purge air is essential as purge air ext
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Abdelfattah, Sherif Alykadry. "Numerical and Experimental Analysis of Multi-Stage Axial Turbine Performance at Design and Off-Design Conditions." Thesis, 2013. http://hdl.handle.net/1969.1/151083.

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Computational fluid dynamics or CFD isan importanttool thatis used at various stages in the design of highly complex turbomachinery such as compressorand turbine stages that are used in land and air based power generation units. The ability of CFD to predict the performance characteristics of a specific blade design is challenged by the need to use various turbulence models to simulate turbulent flows as well as transition models to simulate laminar to turbulent transition that can be observed in various turbomachinery designs. Moreover, CFD is based on numerically solving highly complex diffe
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Books on the topic "Axial turbine stage"

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Escudier, Marcel. Flow through axial-flow-turbomachinery blading. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198719878.003.0014.

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This chapter is concerned primarily with the flow of a compressible fluid through stationary and moving blading, for the most part using the analysis introduced in Chapter 11. The principles of dimensional analysis are applied to determine the appropriate non-dimensional parameters to characterise the performance of a turbomachine. The analysis of incompressible flow through a linear cascade of aerofoil-like blades is followed by the analysis of compressible flow. Velocity triangles for flow relative to blades, and Euler’s turbomachinery equation, are introduced to analyse flow through a rotor
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E, Steinthorsson, Rigby David L, and Lewis Research Center, eds. Effects of tip clearance and casing recess on heat transfer and stage efficiency in axial turbines. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Effects of tip clearance and casing recess on heat transfer and stage efficiency in axial turbines. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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4

United States. National Aeronautics and Space Administration. and United States. Army Aviation Systems Command., eds. Unsteady flows in a single-stage transonic axial-flow fan stator row. National Aeronautics and Space Administration, 1986.

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Book chapters on the topic "Axial turbine stage"

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Lei, Zongqi, Lei Zhao, Weitao Hou, Shiji Wang, and Jing Wang. "Clocking of Stators and Rotors in a Three-Stage Axial Turbine." In Lecture Notes in Electrical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-7423-5_23.

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Subbarao, Rayapati. "Flow Rate and Axial Gap Studies on a One-and-a-Half-Stage Axial Flow Turbine." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1892-8_30.

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Gallus, H. E., C. A. Poensgen, and J. Zeschky. "Three-Dimensional Unsteady Flow in a Single Stage Axial-Flow Turbine and Compressor." 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_24.

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Topalovic, Daniel, Rudibert King, Markus Herbig, Alexander Heinrich, and Dieter Peitsch. "Efficiency Increase and Start-Up Strategy of an Axial Turbine Stage Under Periodic Inflow Conditions Using Extremum Seeking Control." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-90727-3_18.

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Biollo, Roberto, and Ernesto Benini. "State-of-Art of Transonic Axial Compressors." In Advances in Gas Turbine Technology. InTech, 2011. http://dx.doi.org/10.5772/25257.

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"Preliminary Aerodynamic Design of Axial-Flow Turbine Stages." In Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis. ASME Press, 2006. http://dx.doi.org/10.1115/1.802418.ch6.

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"Preliminary Aerodynamic Design of Radial-Inflow Turbine Stages." In Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis. ASME Press, 2006. http://dx.doi.org/10.1115/1.802418.ch10.

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Conference papers on the topic "Axial turbine stage"

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Johnson, Mark S. "One-Dimensional, Stage-by-Stage, Axial Compressor Performance Model." 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-192.

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This paper presents a description of a one-dimensional, constant-radius, stage-by-stage (blade-element) axial compressor model used for compressor map generation and gas turbine off-design performance prediction. This model is designed for investigators who are without access to the proprietary compressor performance information of the gas turbine manufacturers but who are nevertheless interested in predicting the off-design performance of large utility gas turbine power systems. Model performance results (compressor maps) are reported for simulation of a nineteen-stage axial compressor design
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Kumar, S. Satish, Ranjan Ganguli, S. B. Kandagal, and Soumendu Jana. "Flow Behavior in a Transonic Axial Compressor Stage." In ASME 2015 Gas Turbine India Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gtindia2015-1231.

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The steady and unsteady flow characteristics typically vary along and across the axial compressor stage. This coupled with asymmetric rotor tip clearance that occurs in practice makes flow even more complex. Understanding the complex flow behavior inside the transonic compressor stage will aid in developing flow control devices that are meant for purposes such as improving the rotating stall margin, flutter margin, etc. Here, a detailed time averaged numerical analysis is performed on the single stage transonic axial compressor with averaged rotor tip clearance (1.75% of rotor tip axial chord)
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Bloch, Gregory S., and Walter F. O’Brien. "A Wide-Range Axial-Flow Compressor Stage Performance Model." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-058.

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Dynamic compression system response is a major concern in the operability of aircraft gas turbine engines. Multi-stage compression system computer models have been developed to predict compressor response to changing operating conditions. These models require a knowledge of the wide-range, steady-state operating characteristics as inputs, which has limited their use as predicting tools. The full range of dynamic axial-flow compressor operation spans forward and reversed flow conditions. A model for predicting the wide flow range characteristics of axial-flow compressor stages was developed and
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Sell, M., J. Schlienger, A. Pfau, M. Treiber, and R. S. Abhari. "The 2-Stage Axial Turbine Test Facility “LISA”." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0492.

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This paper describes the design and construction of a new two stage axial turbine test facility, christened “Lisa”. The research objective of the rig is to study the impact (relevance) of unsteady flow phenomena upon the aerodynamic performance, this being achieved through the use of systematic studies of parametric changes in the stage geometry and operating point. Noteworthy in the design of the rig is the use of a twin shaft arrangement to decouple the stages. The inner shaft carries the load from the first stage whilst the outer is used with an integral torque-meter to measure the loading
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Louis, J. F. "Axial Flow Contra-Rotating Turbines." In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-218.

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Two types of contra-rotating stages are considered; the first uses guide vanes and the second is vaneless. The wheels of the first type use bladings which are mirror images of each other and they operate with inlet and outlet swirl. The second type uses dissimilar bladings in each of the two wheels with axial inlet velocity to the first wheel and axial outlet velocity for the second wheel. An analysis of their performance indicates that both types can reach stage loading coefficients comparable or larger than conventional turbines with the same number of wheels. A comparison of the contra-rota
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Kumar, S. Satish, Lakshya Kumar, R. Senthil Kumaran, Veera Sesha Kumar, and M. T. Shobhavathy. "Design of High Transonic Axial Compressor Stage for Small Gas Turbine Applications." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2690.

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Abstract In the quest for achieving high performance, gas turbine engines demand efficient design of various engine components, mainly the compressor stages. The compressor stages consume most of the energy produced by the engine to provide the required pressure ratio. CSIR-NAL is involved in the development of a small gas turbine engine for UAV applications. In this regard, a high transonic single stage axial flow compressor is designed with a mass flow of 4.6 kg/s and pressure ratio of 1.6, for technology demonstration. In this paper, the aerodynamic and structural design of a high transonic
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Vashi, Hardik K., Dilipkumar Bhanudasji Alone, and Harish S. Choksi. "Numerically Understanding the Steady State Response of Single Stage Transonic Axial Flow Compressor to Axial Locations of Step for Stepped Tip Clearance." In ASME 2014 Gas Turbine India Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gtindia2014-8147.

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This paper describes the steady state numerical work carried out to study the influence of providing stepped tip clearances at various axial locations along the rotor chord on the performance of the single stage transonic axial compressor. Uniform tip clearance study on compressor under consideration showed performance deterioration of compressor at higher tip clearance of 2mm [3.4% of rotor axial chord] therefore in order to improve performance of compressor, stepped tip clearance method was introduced. Commercially available Ansys Fluent 12.0 software was used to perform steady state RANS si
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Cyrus, Václav. "The Turbine Regime of a Rear Axial Compressor Stage." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-074.

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A detailed investigation of three-dimensional flow has been carried out in a low speed rear axial compressor stage with aspect ratio of 1 at the extreme off-design condition-turbine regime. Measurements were performed by means of both stationery and rotating pressure probes. The mechanism of flow in the rotor and stator blade row in the turbine regime is analysed. Comparison is made with flow mechanism at the design condition.
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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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Chen, Yang, Zhuhai Zhong, Jun Li, et al. "Effect of Stage Axial Distances on the Aerodynamic Performance of Three-Stage Axial Turbine Using Experimental Measurements and Numerical Simulations." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63790.

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The stage axial distance significantly influences the aerodynamic performance of turbines under some constraints. Experimental measurements and numerical simulations are used to analyze the effect of stage axial distances on the aerodynamic performance of three-stage axial turbine in this work. The aerodynamic performance of three-stage axial turbine with three different stage axial distances is experimentally measured at the air turbine test rig of Dongfang Steam Turbine Co. LTD. Experimental results show that efficiency increases when the stage axial distance decreases for the geometry under
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