Relevant bibliographies by topics / Transonic Axial Compressor

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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 'Transonic Axial Compressor'

Author: Grafiati
Published: 6 September 2023

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Journal articles on the topic "Transonic Axial Compressor"

1

Moumen Idres and Muhamad Adi Muqri Saiful Azmi. "Computational Prediction of the Performance Map of a Transonic Axial Flow Compressor." CFD Letters 14, no. 3 (2022): 11–21. http://dx.doi.org/10.37934/cfdl.14.3.1121.

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Aviation fuel efficiency is an important target for aviation industry. Aircraft engine compression ratio is a key factor to improve fuel consumption. Compression ratio can be increased using transonic compressor. In this study, performance prediction of a transonic axial compressor at design and off-design operating conditions is investigated numerically using ANSYS-CFX software. The compressor is NASA Rotor 37. Firstly, the performance at design point is predicted, where mesh independence study is performed to determine suitable mesh size. Three-dimensional flow details for meridional plane,
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Li, Zhihui, and Yanming Liu. "Optimization of rough transonic axial compressor." Aerospace Science and Technology 78 (July 2018): 12–25. http://dx.doi.org/10.1016/j.ast.2018.03.031.

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Meng, Bo, Zhiping Li, Haihui Wang, and Qiushi Li. "An improved wavelet adaptive logarithmic threshold denoising method for analysing pressure signals in a transonic compressor." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 229, no. 11 (2014): 2023–30. http://dx.doi.org/10.1177/0954406214550512.

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This paper proposes an improved wavelet threshold denoising algorithm based on orthogonal wavelet transform. The algorithm, called adaptive logarithmic threshold denoising algorithm based on wavelet (ALTDAW), processes the dynamic pressure signals generated by a transonic axial compressor. Combined with an adaptive logarithmic threshold function, it sets the optimal threshold for each decomposition level. In this way, noise is effectively identified and eliminated. Since ALTDAW is adaptable, it reduces the maximum decomposition level, thereby decreasing the processing time and improving the co
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Calvert, W. J., and R. B. Ginder. "Transonic fan and compressor design." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 213, no. 5 (1999): 419–36. http://dx.doi.org/10.1243/0954406991522671.

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Transonic fans and compressors are now widely used in gas turbine engines because of their benefits in terms of compactness and reduced weight and cost. However, careful and precise design is essential if high levels of performance are to be achieved. In this paper, the evolution of transonic compressor designs and methods is outlined, followed by more detailed descriptions of current compressor configurations and requirements and modern aerodynamic design methods and philosophies. Current procedures employ a range of methods to allow the designer to refine a new design progressively. Overall
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Biollo, Roberto, and Ernesto Benini. "Recent advances in transonic axial compressor aerodynamics." Progress in Aerospace Sciences 56 (January 2013): 1–18. http://dx.doi.org/10.1016/j.paerosci.2012.05.002.

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Liu, Hanru, Yangang Wang, Songchuan Xian, and Wenbin Hu. "Effect of inlet distortion on the performance of axial transonic contra-rotating compressor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 1 (2016): 42–54. http://dx.doi.org/10.1177/0954410016670421.

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The present paper numerically conducted full-annulus investigation on the effects of circumferential total pressure inlet distortion on the performance and flow field of the axial transonic counter-rotating compressor. Results reveal that the inlet distortion both deteriorates the performance of the upstream and downstream rotors resulting in reduction of total pressure ratio, efficiency and stall margin of the transonic contra-rotating compressor. Regarding the development of distortion inside compressor, the downstream rotor reinforces the air-flow mixing effects and, thus, attenuates the di
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Редин, И. И., та М. А. Шевченко. "СИСТЕМАТИЗАЦІЯ І УЗАГАЛЬНЕННЯ ТЕОРЕТИЧНИХ ТА ЕКСПЕРИМЕНТАЛЬНИХ ДАНИХ ПО ЕФЕКТИВНОСТІ НАДРОТОРНОГО ПРИСТРОЮ В ОСЬОВОМУ КОМПРЕСОРІ". Open Information and Computer Integrated Technologies, № 87 (30 червня 2020): 181–99. http://dx.doi.org/10.32620/oikit.2020.87.11.

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The systematization of physical flow models at the peripheral region of the rotors of axial compressor is carried out. Based on the experimental and numerical studies, the flow features in subsonic and transonic rotors are analyzed. Similar features of the flow near the wall at the periphery of subsonic and transonic rotors are formulated. The characteristic areas and individual features of the near-wall flow in them, which are obtained in experimental studies of the flow structure at the periphery of the blade rows, are reflected. The analysis of the influence of annular grooves in the axial
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Law, C. H., and A. J. Wennerstrom. "Performance of Two Transonic Axial Compressor Rotors Incorporating Inlet Counterswirl." Journal of Turbomachinery 109, no. 1 (1987): 142–48. http://dx.doi.org/10.1115/1.3262059.

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A single-stage axial-flow compressor which incorporates rotor inlet counterswirl to improve stage performance is discussed. Results for two rotor configurations are presented, including design and experimental test data. In this compressor design, inlet guide vanes were used to add counterswirl to the inlet of the rotor. The magnitude of the counterswirl was radially distributed to maximize the overall stage efficiency by minimizing the rotor combined losses (diffusion losses and shock losses). The shock losses were minimized by simultaneously optimizing the rotor blade section geometry, throu
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Rabe, D. C., A. J. Wennerstrom, and W. F. O’Brien. "Characterization of Shock Wave–Endwall Boundary Layer Interactions in a Transonic Compressor Rotor." Journal of Turbomachinery 110, no. 3 (1988): 386–92. http://dx.doi.org/10.1115/1.3262208.

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The passage shock wave–endwall boundary layer interaction in a transonic compressor was investigated with a laser transit anemometer. The transonic compressor used in this investigation was developed by the General Electric Company under contract to the Air Force. The compressor testing was conducted in the Compressor Research Facility at Wright-Patterson Air Force Base, OH. Laser measurements were made in two blade passages at seven axial locations from 10 percent of the axial blade chord in front of the leading edge to 30 percent of the axial blade chord into the blade passage. At three of t
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Kodama, H. "Performance of Axial Compressor With Nonuniform Exit Static Pressure." Journal of Turbomachinery 108, no. 1 (1986): 76–81. http://dx.doi.org/10.1115/1.3262027.

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An analytical model has been developed to predict the performance of axial compressors with an exit static pressure perturbation. The model uses a two-dimensional compressible semi-actuator disk model. This method can be applied to the compressor with known circumferential variation in exit static pressure which is measured or predicted by an analytical method. The analytical results are found to be in good agreement with experiments carried out on two transonic fans.
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Dissertations / Theses on the topic "Transonic Axial Compressor"

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Grossman, Bart L. "Testing and analysis of a transonic axial compressor." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA341113.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 1997.<br>"September 1997." Thesis advisor(s): Raymond P. Shreeve. Includes bibliographical references (p. 57). Also available online.
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Sadek, Joseph. "Effect of Axial Gap Distance on Transonic Compressor Performance." Thesis, KTH, Kraft- och värmeteknologi, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-172994.

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The modern trend of gas turbines design is towards lighter, highly efficient,and more compact engines. Such situation imposes on engineers to continuouslysearch for improved and optimum designs. The thesis presented aims at researching possible performance improvements regarding axial gapdistance in transonic compressors. Decreasing the axial gap would result inlighter engines and achieve design goals. The influence of decreasing the axialgap on performance and structure integrity should be throughly analyzed. This thesis work includes numerical investigations on the axial gap distance effect
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Reid, William D. "Transonic axial compressor design case study and preparations for testing." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA306259.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 1995.<br>Thesis advisor(s): Raymond P. Shreeve. "September 1995." Includes bibliographical references. Also available online.
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Cahill, Joseph E. "Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction." Thesis, Virginia Tech, 1997. http://hdl.handle.net/10919/37041.

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The correlation of cascade experimental data is one method for obtaining compressor stage characteristics. These correlations specify pressure loss and flow turning caused by the blades. Current open literature correlations used in streamline curvature codes are inadequate for general application to high-speed transonic axial-flow compressors. The objective of this research was to investigate and evaluate the available correlations and ultimately discover sets of correlations which best fit the empirical data to be used in streamline curvature codes. Correlations were evaluated against exp
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Drayton, Scott. "Design, test, and evaluation of a transonic axial compressor rotor with splitter blades." Thesis, Monterey, California: Naval Postgraduate School, 2013. http://hdl.handle.net/10945/37616.

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Approved for public release; distribution is unlimited<br>A new design procedure was developed and documented that uses commercial-off-the-shelf software (MATLAB, SolidWorks, and ANSYS-CFX) for the geometric rendering and analysis of a transonic axial compressor rotor with splitter blades. Predictive numerical simulations were conducted and experimental data were collected at the NPS TPL utilizing the Transonic Compressor Rig. This study advanced the understanding of splitter blade geometry, placement, and performance benefits. In particular, it was determined that moving the splitter blade fo
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Weigl, Harald Jürgen. "Active stabilization of rotating stall and surge in a transonic single stage axial compressor." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/10353.

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Ryman, John Franklin. "Prediction of Inlet Distortion Transfer Through the Blade Rows in a Transonic Axial Compressor." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/43207.

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Inlet total pressure non-uniformities in axial flow fans and compressors can contribute to the loss of component structural integrity through high cycle fatigue (HCF) induced by the excitation of blade vibratory modes. As previous research has shown total pressure distortion to be the dominant HCF driver in aero engines [Manwaring et al, 1997], an understanding of its transfer through, and impact on, subsequent turbomachine stages and engine components is an important topic for assessment. Since current modeling techniques allow for total pressure distortion magnitudes to be directly related
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Jones, James A. "A multidisciplinary algorithm for the 3-D design optimization of transonic axial compressor blades." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Jun%5FJones%5FJames.pdf.

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Thesis (Ph. D. in Aeronautics and Astronautics)--Naval Postgraduate School, June 2002.<br>Dissertation supervisor: Raymond P. Shreeve. Includes bibliographical references (p. 157-161). Also available online.
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Heinlein, Gregory S. "Aerodynamic Behavior of Axial Flow Turbomachinery Operating in Transient Transonic Flow Regimes." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1573149943024303.

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Figueiredo, Josué Sanches. "Determination of stall and choke limits of a transonic axial flow compressor using the straemline curvature method." Instituto Tecnológico de Aeronáutica, 2010. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2090.

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The necessity for high performance axial compressors for various applications is shown. The basic theory associated with the study of these machines is presented. A method for calculating the properties of the flow along the compressor is presented. Depending on the design requirements the number of stages is selected and an appropriate shape of the channel studied. Then the compressor blading is made, row-by-row, from the calculation of the flow using a non-viscous flow associated with a loss model that allows, from the known flow at the leading edge, calculate the flow at the trailing edge.
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Books on the topic "Transonic Axial Compressor"

1

United States. National Aeronautics and Space Administration., ed. Blockage development in a transonic, axial compressor rotor. National Aeronautics and Space Administration, 1997.

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United States. National Aeronautics and Space Administration., ed. Blockage development in a transonic, axial compressor rotor. National Aeronautics and Space Administration, 1997.

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3

Grossman, Bart L. Testing and analysis of a transonic axial compressor. Naval Postgraduate School, 1997.

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Neuhoff, F. Modifications to the inlet flow field of a transonic compressor rotor. Naval Postgraduate School, 1985.

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United States. National Aeronautics and Space Administration., ed. Experimental determination of aerodynamic damping in a three-syage transonic axial-flow compressor. National Aeronautics and Space Administration, 1988.

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Newman, Frederick A. Experimental vibration damping characteristics of the third-stage rotor of a three-stage transonic axial-flow compressor. National Aeronautics and Space Administration, 1988.

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L, Suder Kenneth, and United States. National Aeronautics and Space Administration., eds. The effect of adding roughness and thickness to a transonic axial compressor rotor. National Aeronautics and Space Administration, 1995.

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L, Celestina Mark, and United States. National Aeronautics and Space Administration., eds. Experimental and computational investigation of the tip clearance flow in a transonic axial compressor rotor. National Aeronautics and Space Administration, 1995.

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Chung-hua, Wu. A general theory of two-and three-dimensional rotational flow in subsonic and transonic turbomachines. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Chung-hua, Wu. A general theory of two-and three-dimensional rotational flow in subsonic and transonic turbomachines. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Book chapters on the topic "Transonic Axial Compressor"

1

Barthmes, Sebastian, Jakob P. Haug, Andreas Lesser, and Reinhard Niehuis. "Unsteady CFD Simulation of Transonic Axial Compressor Stages with Distorted Inflow." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-21127-5_18.

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Iseler, Jens, Andreas Lesser, and Reinhard Niehuis. "Numerical Investigation of a Transonic Axial Compressor Stage with Inlet Distortions." In High Performance Computing in Science and Engineering, Garching/Munich 2009. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-13872-0_16.

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Nha, Tuong-Linh, Van-Hoang Nguyen, Xuan-Truong Le, and Cong-Truong Dinh. "Aerodynamic Performance of Single-Stage Transonic Axial Compressor with Multi-Bleed Airflow." In Lecture Notes in Mechanical Engineering. Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-31824-5_14.

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Yu, S., G. H. Schnerr, U. Dohrmann, and O. Sadi. "Passive control of shock-boundary layer interaction in transonic axial compressor cascade flow." In Fluid- and Gasdynamics. Springer Vienna, 1994. http://dx.doi.org/10.1007/978-3-7091-9310-5_24.

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Huang, N. Z., X. Zhao, and Y. H. Zhang. "The Swept and Leaned Blade Influence on the Aerodynamic Performance of a Transonic Axial Compressor Rotor." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_18.

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Zhao, Xuning, Xuhui Zhou, Jinxin Cheng, and Jiang Chen. "Numerical Investigation on Arbitrary Polynomial Blade Model for a Transonic Axial-Flow Compressor Rotor with Multi-parameter Optimization." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_2.

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Hofmann, Willy, and Josef Ballmann. "Tip-Vortices in Transonic Axial-Compressors." In New Results in Numerical and Experimental Fluid Mechanics III. Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/978-3-540-45466-3_41.

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Pitroda, Darshan P., Dilipkumar Bhanudasji Alone, and Harish S. Choksi. "Understanding of an Effect of Plenum Volume of a Low Porosity Bend Skewed Casing Treatment on the Performance of Single-Stage Transonic Axial Flow Compressor." In Proceedings of the National Aerospace Propulsion Conference. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_1.

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Du, W. H., H. Wu, and L. Zhang. "Off-design Performance Analysis of Multi-Stage Transonic Axial Compressors." In New Trends in Fluid Mechanics Research. Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-75995-9_167.

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Dalbanjan, Manjunath S., and Niranjan Sarangi. "Sensitivity Study of Stagger Angle on the Aerodynamic Performance of Transonic Axial Flow Compressors." In Proceedings of the National Aerospace Propulsion Conference. Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2378-4_1.

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Conference papers on the topic "Transonic Axial Compressor"

1

Suder, Kenneth L. "Blockage Development in a Transonic, Axial Compressor Rotor." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-394.

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A detailed experimental investigation to understand and quantify the development of blockage in the flow field of a transonic, axial flow compressor rotor (NASA Rotor 37) has been undertaken. Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor operating at 100%, 85%, 80%, and 60% of design speed which provided inlet relative Mach numbers at the blade tip of 1.48, 1.26, 1.18, and 0.89 respectively. The impact of the shock on the blockage development, pertaining to both the shock / boundary layer interactions and the shock
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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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Siller, Ulrich, Christian Voß, and Eberhard Nicke. "Automated Multidisciplinary Optimization of a Transonic Axial Compressor." In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-863.

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Li, Tao, Yadong Wu, Hua Ouyang, and Xiaoqing Qiang. "Axial Compressor Performance Prediction Using Improved Streamline Curvature Approach." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75450.

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This paper presents in detail the improved streamline curvature approach (SLC) to the performance evaluation and internal flow field calculation of subsonic and transonic axial compressors. Based on previous research, the diverse incidence, deviation and total pressure loss models, generally existing in the form of fitting curves and semi-empirical correlations, are discussed respectively. Typically, transonic flow in axial compressor results in the variation of several flow parameters and particularly the appearance of shock waves compared with subsonic flow. In this paper, the revision and i
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Law, C. Herbert, and Arthur J. Wennerstrom. "Performance of Two Transonic Axial Compressor Rotors Incorporating Inlet Counterswirl." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-33.

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A single-stage axial-flow compressor which incorporates rotor inlet counterswirl to improve stage performance is discussed. Results for two rotor configurations are presented, including design and experimental test data. In this compressor design, inlet guide vanes were used to add counterswirl to the inlet of the rotor. The magnitude of the counterswirl was radially distributed to maximize the overall stage efficiency by minimizing the rotor combined losses (diffusion losses and shock losses). The shock losses were minimized by simultaneously optimizing the rotor blade section geometry, throu
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Kaur, Baljeet, Nitin B. Balsaraf, and Ajay Pratap. "A Study of Existing Multistage Transonic Axial Compressor Design for Surge Margin Improvement." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3616.

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The design of multistage axial flow compressors has been revolutionised in recent years by the development of three dimensional multistage viscous calculations (CFD) and the availability of the computational power to allow these methods to be used extensively in design process. Such a multistage turbomachinery was used to redesign the existing three stage transonic compressor for improved aerodynamic performance in terms of SM limit. The redesign activity of compressor configuration was carried out as surge margin obtained with hardware testing of existing machinery was not sufficient to meet
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Zhang, Xiawen, Yaping Ju, Chuhua Zhang, Cong Li, and Dejun Meng. "Geometry Scaling Technique For Aerodynamic Redesign Of Multistage Transonic Compressor." In GPPS Xi'an21. GPPS, 2022. http://dx.doi.org/10.33737/gpps21-tc-240.

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The aerodynamic design of multi-stage transonic axial-flow compressors plays a critical role in the overall performance of aeronautical engine, gas turbine and industry compression unit. Despite a series of new design methods have been successfully proposed in the research and development of advanced axial-flow compressors, redesign methods are still one of the most effective measures in the development of available advanced products to meet new requirements. In this work, a geometry scaling technique is proposed in which 1D mean-line analysis and 3D parametric geometric modeling are used to d
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Manfredi, Marco, Cedric Babin, and Fabrizio Fontaneto. "Transonic Axial Compressors Loss Correlations: Part II — Loss Models Validation." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-16131.

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Abstract The quest for greener, more efficient aircraft engines is the main driver for the development of innovative compression system designs. Reduced order design tools rely nevertheless on semi-empirical loss models, whose validity range is often not net or in general not verified. The present work aims at defining a set of loss correlations, which could readily be employed in the analysis and design process of modern transonic axial compressors. In Part I, various loss correlations were deeply described and, in some cases, updated to enhance both their generality and their prediction capa
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Shahpar, Shahrokh, Andrey Polynkin, and Vassili Toropov. "Large Scale Optimization of Transonic Axial Compressor Rotor Blades." In 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16th AIAA/ASME/AHS Adaptive Structures Conference
10t. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2056.

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Li, Qiushi, Tianyu Pan, Zhiping Li, Tailu Sun, and Yifang Gong. "Experimental Study of Compressor Instability Inception in a Transonic Axial Flow Compressor." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25190.

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An experimental investigation is conducted to study the details of instability inception in a transonic axial flow compressor. The experimental results indicate that the compressor instability is initiated through the development of a low-frequency axisymmetric disturbance. The frequency of this disturbance is approximately the Helmholtz frequency of the test facility. The low-frequency disturbance can be detected over 3000 rotor revolutions before the compressor becomes unstable. Further experimental investigations illustrate that this low-frequency axisymmetric disturbance is initiated at th
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Reports on the topic "Transonic Axial Compressor"

1

Chen, Jen-Ping, Michael D. Hathaway, and Gregory P. Herrick. Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation. Defense Technical Information Center, 2008. http://dx.doi.org/10.21236/ada500494.

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