Abstract
This article conducted flow field refinement tests on a high load compressor using steady-state five hole probes, high-frequency dynamic probes, and blade probes, and obtained detailed inter stage flow field characteristics such as total pressure, total temperature, and Mach number. The results showed that by analyzing and comparing the flow field parameters of the compressor’s overall performance and inter stage performance tests with CFD design performance, the main characteristics that affect compressor performance can be effectively obtained, Obtain the flow field performance of the blade near the end wall and upstream and downstream blades, among which the steady-state five hole probe and dynamic single hole probe effectively overcome the problem of limited conventional measurement space for the compressor; The blade probe obtained detailed flow field distributions of performance parameters along the radial and circumferential directions of the 1–3 stage rotor, providing experimental data support for compressor flow field diagnosis and performance optimization.
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References
Peng, Z., Liu, G.: Principles of aviation gas turbine, pp. 66–68. National Defense Industry Press, Beijing (2000). (in Chinese)
Fei, Y., Liu, Y., Lu, L.: Modification of realizable κ-ε model for tip-leakage flow in an axial compressor rotor. J. Eng. Thermophys. 40(3), 505–512 (2019)
Chen, M., Liu, B.: Fan/compressor aero design trend and challenge on the development of high bypass ratio turbofan. J. Aerosp. Power 23(6), 961–975 (2008)
David, J.: Advanced experimental techniques in turbomachinery, pp. 22–25. Concepts Eti., Norwich (1986)
Liu, Q., Zhou, X.: Numerical analysis of three-dimensional viscous flow through multistage fan and compressors. J. Eng. Thermophys. 22(4), 52–55 (2001). (in Chinese)
Sun, H., Ye, N., Wang, J., et al.: Effect of tip clearance on axial compressor performance and flow field. Aeroengine 40(3), 1–7 (2014). (in Chinese)
Jiang, H., et al.: The experimental device and dynamic measurement technology of large-size axial compressor flowing in the rotor were studied. J. Aerodyn. 1 (1992)
Denton, J.D.: Some limitations of turbomachinery CFD. ASME Turbo Expo Power for Land Sea & Air, Glasgow, No. GT2010-22540, pp. 735–745 (2010)
Ye, D., Yuan, X.: Development of flow field diagnostics. In: Compilation of Special Reports of the Symposium on Development Strategy of Aerothermodynamics, pp. 126–130 (1989)
Roberts, W.B., Serovy, G.K., Sandercock, D.M.: Modeling the 3-D Flow Effects on Deviation Angle for Axial Compressor Middle Stages. ASME paper85-GT-189 (1985)
Li, J., Ma, H., He, X.: Method of measuring 3-D unsteady flow at exits of transonic compressor rotor passages using a two-hole tip-wedge pressure probe. J. Aerosp. Power 27(10), 2262–2268 (2012)
Ma, H., Wei, W., Zhang, L., Guan, H.: Analysis of measured unsteady flow field using a quasi fast response pressure probe. Aeroengine 42(2), 67–72 (2016)
Zhao, Q., Duan, L., Shen, P.: HB7115-94 compressor aerodynamic performance test, pp. 2–7. China Aviation Industry Corporation, Beijing (1995). (in Chinese)
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Wang, A., Zhang, Z., Chen, Y., Wang, X. (2024). Diagnosis and Analysis of Interstage Flow Field in a High Load Compressor. In: Proceedings of the 6th China Aeronautical Science and Technology Conference. CASTC 2023. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-99-8867-9_14
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DOI: https://doi.org/10.1007/978-981-99-8867-9_14
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