An Off-Design Flow Angle Model Based on Average-Flow Theory and Wake Analysis

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  • Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China

Online published: 2023-11-28

Supported by

This work is funded through the National Science and Technology Major Project (2017-III-0009-0035) and National Natural Science Foundation of China (Grant No. 52276031).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023

Abstract

This paper presents a novel model for flow angles at off-design conditions. The model is based on energy conservation in turbomachinery. By the mean of average process, statistical properties of the wake profile are related to the flow angle and mainstream parameters; then by adopting the classic flow topology of behind-blade wakes, the effect of operating conditions is included in the plot and a model for flow angle is thus developed. The advantage of the model is that it can achieve off-design flow angle estimations with design flow characteristics and it is compatible with CFD-based throughflow methods. This model is then implemented into a standard CFD-based throughflow solver from the previous research to estimate off-design characteristics of blade rows with proper input-output strategies. Furthermore, the effect of loss upon flow angle is also modeled as corrections to the proposed model. The model is validated on a compressor stage and the results show promising accuracy for off-design flow angle estimations.

Cite this article

MAO Yinbo, SU Xinrong, YUAN Xin . An Off-Design Flow Angle Model Based on Average-Flow Theory and Wake Analysis[J]. Journal of Thermal Science, 2023 , 32(2) : 729 -738 . DOI: 10.1007/s11630-023-1774-2

References

[1] Mao Y., Dang T.Q., Simple approach for modeling fan systems with a computational-fluid-dynamics-based body-force model. Journal of Propulsion and Power, 2020, 36(5): 1–13. DOI: 10.2514/1.B37742.
[2] Wu C.H., A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial, radial, and mixed-flow types. Journal of Fluids Engineering, 1952, 74(8): 1363–1380.
[3] Qiu X., Japikse D., Zhao J., Anderson M.R., Analysis and validation of a unified slip factor model for impellers at design and off-design conditions. Journal of Turbomachinery, 2011, 133(4): 041018. DOI: 10.1115/1.4003022.
[4] Simon J.F., Léonard O., Modeling of 3-D losses and deviations in a throughflow analysis tool. Journal of Thermal Science, 2007, 16(3): 208–214. DOI: 10.1007/s11630-007-0208-x.
[5] Lieblein S., Incidence and deviation-angle correlations for compressor cascades. Journal of Basic Engineering, 1960, 82(3): 575–584. DOI: 10.1115/1.3662666.
[6] Lieblein S., Experimental flow in 2D cascades. 1965, NASA TP-SP36.
[7] Dixon S.L., Hall C.A., Fluid mechanics and thermodynamics of turbomachinery, 7th Ed., 2014, Butterworth-Heinemann, Oxford, UK.
[8] Cetin M., Uecer A.S., Hirsch C.H.A.R.L.E.S., Serovy G.K., Application of modified loss and deviation correlations to transonic axial compressors. Advisory Group for Aerospace Research and Development (AGARD), 1987, Neuilly-Sur-Seine, France.
[9] König W.M., Hennecke D.K., Fottner L., Improved blade profile loss and deviation angle models for advanced transonic compressor bladings: Part I—A model for subsonic flow. Journal of Turbomachinery, 1996, 118(1): 73–80. DOI: 10.1115/1.2836609.
[10] König W.M., Improved blade profile loss and deviation angle models for advanced transonic compressor bladings: Part II—A model for supersonic flow. Journal of Turbomachinery, 1996, 118(1): 81–87. DOI: 10.1115/1.2836610.
[11] Wennestrom A.J., Design of highly loaded axial-flow fans and compressors. 2000, Concepts ETI, White River Junction, Vermont, USA.
[12] Johnsen I.A., Bullock R.O., Aerodynamic design of axial-flow compressors. 1965, NASA SP-36.
[13] Raj R., Lakshminarayana B., Characteristics of the wake behind a cascade of airfoils. Journal of Fluid Mechanics, 1973, 61(4): 707–730. DOI: 10.1017/S002211207300090X.
[14] Denton J.D., The calculation of three-dimensional viscous flow through multistage turbomachines. Journal of Turbomachinery, 1992, 114(1): 18–26. DOI: 10.1115/1.2927983.
[15] Mao Y., Body force modeling for engine inlet fan system. Department of Mechanical and Aerospace Engineering, Syracuse University, Syracuse, NY, 2018.
[16] Mao Y., Dang T.Q., A three-dimensional body-force model for nacelle-fan systems under inlet distortions. Aerospace Science and Technology, 2020, 106: 106085. DOI: 10.1016/j.ast.2020.106085.
[17] Jennions I.K., Stow P., A quasi-three-dimensional turbomachinery blade design system: part I—throughflow analysis. Journal Engineering for Gas Turbines and Power, 1985, 107(2): 301–307. DOI: 10.1115/1.3239715.
[18] Adamczyk J.J., Model equation for simulating flows in multistage turbomachinery. 1984, NASA TM-86869.
[19] Schlichting H., Boundary layer theory. 2017, Springer-Verlag, Berlin, Heidelberg.
[20] Damle S.V., Dang T.Q., Reddy D.R., Throughflow method for turbomachines applicable for all flow regimes. Journal Engineering for Gas Turbines and Power, 1997, 119(2): 256–262. DOI: 10.1115/1.2841108
[21] Sturmayr A., Hirsch C., Throughflow model for design and analysis integrated in a 3D Navier-Stokes solver. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 1999, 213(4): 263–273.
[22] Emery J.C., Herrig L.J., Erwin J.R., Felix A.R., Systematic two-dimensional cascade tests of NACA 65-Series compressor blades at low speed. 1958, NACA Report No. 1368.
[23] Sarimurat M.N., Dang T.Q., An analytical model for boundary layer control via steady blowing and its application to NACA-65-410 cascade. Journal Engineering for Gas Turbines and Power, 2014, 136(6): 061011. DOI: 10.1115/1.4025585.
[24] Reid L., Moore R.D., Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor. 1978, NASA TP-1337.
[25] Seshadri P., Parks G.T., Shahpar S., Leakage uncertainties in compressors: the case of Rotor 37. Journal of Propulsion and Power, 2015, 31(1): 456–466. DOI: 10.2514/1.B35039.
[26] Dalbert P., Wiss D.H., Numerical transonic flow field predictions for NASA compressor Rotor 37. ASME Turbo Expo: Power for Land, Sea, and Air, 1995, Paper No. 95-GT-326. DOI: 10.1115/95-GT-326.
[27] Denton, J.D., Lessons from Rotor 37. Journal of Thermal Science, 1997, 6(1): 1–13. DOI: 10.1007/s11630-997-0010-9.
[28] Ameri, A., NASA Rotor 37 CFD code validation. 2010, NASA CR-2010-216235.
[29] Suder K.L., Experimental investigation of the flow field in a transonic, axial flow compressor with respect to the development of blockage and loss. 1996, NASA TM-107310.
[30] Bosman C., Marsh H., An improved method for calculating the flow in turbo-machines, including a consistent loss model. Journal of Mechanical Engineering Science, 1974, 16(1): 25–31. DOI: 10.1243/jmes_jour_1974_016_006_02.
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