Tip leakage vortex (TLV) has a large impact on compressor performance and should be accurately predicted by computational fluid dynamics (CFD) methods. New approaches of turbulence modeling, such as delayed detached eddy simulation (DDES), have been proposed, the computational resources of which can be reduced much more than for large eddy simulation (LES). In this paper, the numerical simulations of the rotor in a low-speed large-scale axial compressor based on DDES and unsteady Reynolds-averaged Navier–Stokes (URANS) are performed, thus improving our understanding of the TLV dynamic mechanisms and discrepancy of these two methods. We compared the influence of different time steps in the URANS simulation. The widely used large time-step makes the unsteadiness extremely weak. The small time-step shows a better result close to DDES. The time-step scale is related to the URANS unsteadiness and should be carefully selected. In the time-averaged flow, the TLV in DDES dissipates faster, which has a more similar structure to the experiment. Then, the time-averaged and instantaneous results are compared to divide the TLV into three parts. URANS cannot give the loss of stability and evolution details of TLV. The fluctuation velocity spectra show that the amplitude of high frequencies becomes obvious downstream from the TLV, where it becomes unstable. Last, the anisotropy of the Reynolds stress of these two methods is analyzed through the Lumley triangle to see the distinction between the methods and obtain the Reynolds stress. The results indicate that the TLV latter part in DDES is anisotropic, while in URANS it is isotropic.
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Research-Article
Comparison of DDES and URANS for Unsteady Tip Leakage Flow in an Axial Compressor Rotor
Yangwei Liu
,
Yangwei Liu
National Key Laboratory of Science and
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: liuyangwei@126.com
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: liuyangwei@126.com
1
Corresponding author.
Search for other works by this author on:
Luyang Zhong
,
Luyang Zhong
National Key Laboratory of Science and
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China
e-mail: buaa.zly@qq.com
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China
e-mail: buaa.zly@qq.com
Search for other works by this author on:
Lipeng Lu
Lipeng Lu
National Key Laboratory of Science and
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: lulp@buaa.edu.cn
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: lulp@buaa.edu.cn
Search for other works by this author on:
Yangwei Liu
National Key Laboratory of Science and
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: liuyangwei@126.com
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: liuyangwei@126.com
Luyang Zhong
National Key Laboratory of Science and
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China
e-mail: buaa.zly@qq.com
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China
e-mail: buaa.zly@qq.com
Lipeng Lu
National Key Laboratory of Science and
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: lulp@buaa.edu.cn
Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beihang University,
Beijing 100191, China
e-mail: lulp@buaa.edu.cn
1
Corresponding author.
Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received December 17, 2018; final manuscript received April 28, 2019; published online June 17, 2019. Assoc. Editor: Sergio Pirozzoli.
J. Fluids Eng. Dec 2019, 141(12): 121405 (13 pages)
Published Online: June 17, 2019
Article history
Received:
December 17, 2018
Revised:
April 28, 2019
Citation
Liu, Y., Zhong, L., and Lu, L. (June 17, 2019). "Comparison of DDES and URANS for Unsteady Tip Leakage Flow in an Axial Compressor Rotor." ASME. J. Fluids Eng. December 2019; 141(12): 121405. https://doi.org/10.1115/1.4043774
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