Probing Into the Connotation of Sweep Aerodynamics of Transonic Fans and Compressors

Xing, Xiuqing; Zhou, Sheng; Zhao, Xiaolu

doi:10.1115/2001-gt-0352

Cited by 6 publications

(7 citation statements)

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“…Use of the axial location is convenient during the airfoil design process [16] because the change in the axial location impacts the shifting of the sections grav- ity center location, which again impacts blade structure frequency and stresses. In most of the sweep airfoil studies, the airfoil chord lengths were changed in some sections [9,11] and the locations of the airfoil base section were also changed, making it di©cult to see the aerodynamic sweep e¨ects whether it is coming from the sweep or from the section changes. In this study, the base sections were ¦xed.…”

Section: Calculationsmentioning

confidence: 99%

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Computations of flows over a turbine blade

Amano¹,

Xu²

2009

Progress in Propulsion Physics

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To meet the needs of e©cient turbine blade designs, computational §uid dynamics (CFD) predictions of a complex three-dimensional (3D) §ow ¦eld in turbine blade passages have been incorporated in the design process during the last decade. Owing to the numerous advantages possessed by a 3D CFD technology, many industries already use a 3D blading technique in the design process of turbomachines. In addition, blade lean and sweep have been implemented to increase the blade row e©ciency. Experimental studies have shown some advantages of these features. However, most of the experimental results were combined with other features together as well, thus making it di©cult to determine the e¨ects of individual superior features. The development of CFD techniques has made it possible to do 3D turbulent §ow analyses in a very short time. In this study, numerical studies are presented to demonstrate the sweep e¨ects on a transonic compressor airfoil. The purpose of this study is to investigate the sweep e¨ects without changing other compressor blade features, i.e., keeping the blade out §ow angles and section shapes to be the same at design sections for all cases. Through this study, the sweep e¨ect in a transonic compressor rotor blade was tested. The results showed that the sweeps redistribute the §ow reducing the secondary §ow loss, depending on the baseline. It was shown that the forward sweep reduces the tip loading in terms of the static pressure coe©cient.

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Section: Calculationsmentioning

confidence: 99%

“…The study by Xing et al [11] showed that a stall margin of the back-sweep is about the same as that of an unswept rotor blade. These studies show that the e¨ect of sweep on transonic compressors is not fully understood.…”

Section: Introductionmentioning

confidence: 97%

Computations of flows over a turbine blade

Amano¹,

Xu²

2009

Progress in Propulsion Physics

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“…Conversely, the forward sweep could increase the stall margin. The study by Xing et al [12] showed that a stall margin of the back sweep is about the same as that of the unswept rotor blade. Clearly, the effects of sweep on transonic compressors are not fully understood.…”

Section: Introductionmentioning

confidence: 96%

“…There are not many detailed descriptions of sweeps and whether other design parameters change or not when sweeps were implemented. Most studies [10][11][12] did not report whether the test flow boundary conditions were the same for all sweeps and unsweeps. Much research still needs to be done to better understand sweep blades in the future.…”

Section: Introductionmentioning

confidence: 99%

Computational Analysis of Swept Compressor Rotor Blades

Amano

2008

International Journal for Computational Methods in Engineering

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Three-dimensional blading has been used in the process of turbomachine designs. To meet the need for efficient turbine blade designs, CFD predictions of a complex 3D flow field in turbine blade passages had been used. Because the numerous advantages of 3D CFD have been reported in the open literature, many industries already use 3D blading in their turbomachines. In addition, blade lean and sweep have been implemented to increase the blade row efficiency. Experimental studies have shown the advantages of these features. However, most of the experimental results combined other features together, which is difficult to determine the effects of individual features. The development of the CFD technique had made it possible to do three-dimensional turbulent flow analyses in a very short time. In this study, the numerical studies are presented to study the sweep effects of a transonic compressor airfoil. The focus of the paper is to investigate the sweep effects without changing the compressor blade's other features, i.e. keeping the blade outflow angle the same for all the cases. The purpose of the study is to enhance the understanding of the sweep in a transonic compressor rotor blade. The results show that the sweeps redistribute the flow, which may reduce the secondary flow loss depending on the baseline. It is shown that forward sweep reduces the tip loading in terms of static pressure coefficient.

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“…Hah, Copenhaver, Puterbaugh and Wadia [6] used aerodynamic sweep to control shock structure and secondary flow field of a transonic compressor rotor. Denton and Xu [7], Xu and Chen [8], Xing, Zhou and Zhao [9] through numerical computational method studied the sweep effect on performance in fans and compressors. Therefore, it is seem clearly that study on blade sweeping has become one of the important research projects.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic sweeping study and design for transonic compressor rotor blades

2010

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The objective of the present paper is to study the sweep effect on the blade design performance of a transonic compressor rotor. The baseline to be modified and swept is a designed well efficient transonic single rotor compressor. The first part of the present study is concerning the sweep effect with straight leading edge. In this case fixing the hub section the swept blade is formed by tilting the leading edge with whole blade forwards and backwards axially. The second part is to use an optimization strategy with simple gradient-based optimum-searching method and multi-section blade parameterization technique to search and generate an optimal swept rotor with curved arbitrary leading edge. Its adiabatic efficiency is a little bit greater than that of the reference un-swept rotor.

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Probing Into the Connotation of Sweep Aerodynamics of Transonic Fans and Compressors

Cited by 6 publications

References 0 publications

Computations of flows over a turbine blade

Computations of flows over a turbine blade

Computational Analysis of Swept Compressor Rotor Blades

Aerodynamic sweeping study and design for transonic compressor rotor blades

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