[1]
Lieblein S., Analysis of experimental low-speed loss and stall characteristics of two-dimensional compressor blade cascades. NASA Research Memorandum, paper NACA-RM-E57A28, 1957.
[2]
Herrig L.J., Emery J.C., Erwin J.R., Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds. Langley Aeronautical Laboratory, 1957.
[3]
Hausmann G.F., The theoretical induced deflection angle in cascades having wall boundary layers. Journal of the Aeronautical Sciences, 1948, 15(11): 686‒690.
[4]
Lieblein S., Incidence and deviation-angle correlations for compressor cascades. Journal of Basic Engineering, 1960, 82(3): 575‒584.
[5]
Hobbs D.E., Weingold H.D., Development of controlled diffusion airfoils for multistage compressor application. Journal of Engineering for Gas Turbines and Power, 1984, 106(2): 271‒278.
[6]
Steinert W., Eisenberg B., Starken H., et al., Design and testing of a controlled diffusion airfoil cascade for industrial axial flow compressor application. Journal of Turbomachinery, 1991, 113(4): 583‒590.
[7]
Dring R.P., Joslyn H.D., Hardin L.W., et al., An investigation of axial compressor rotor aerodynamics. Journal of Engineering for Power, 1982, 104(1): 84‒96.
[8]
Schulz H.D., Gallus H.E., Lakshminarayana B., et al., Three-dimensional separated flow field in the endwall region of an annular compressor cascade in the presence of rotor-stator interaction: part I—Quasi-steady flow field and comparison with steady-state data. Journal of Turbomachinery, 1990, 112(4): 669‒678.
[9]
Konig 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.
[10]
Louis J.F., Secondary flow and losses in a compressor cascade. Aeronautical Research Council, Great Britain, No.3136 HM Stationery Office, 1960.
[11]
Cyrus V., Experimental investigation of losses and secondary flow in an axial compressor stage. Forschung Im Ingenieurwesen, 1985, 51(2): 33‒40.
[12]
Inoue M., Kuroumaru M., Structure of tip clearance flow in an isolated axial compressor rotor. Journal of Turbomachinery, 1989, 111(3): 250‒256.
[13]
Gray S., Paper 17: Stage matching, stall, and surge in multi-stage axial flow compressors. Proceedings of the Institution of Mechanical Engineers, Conference Proceedings. Sage UK: London, England: SAGE Publications, 1969, 184(7): 49‒56.
DOI: 10.1243/PIME_CONF_1969_184_182_02.
[14]
Escuret J.F., Garnier V., Stall inception measurements in a high-speed multistage compressor. Journal of Turbomachinery, 1996, 118(4): 690‒696.
[15]
Halstead D.E., Wisler D.C., Okiishi T.H., et al., Boundary layer development in axial compressors and turbines: Part 2 of 4—Compressors. Journal of Turbomachinery, 1997, 119(3): 426‒444.
[16]
Mailach R., Vogeler K., Aerodynamic blade row interactions in an axial compressor—Part I: Unsteady boundary layer development. Journal of Turbomachinery, 2004, 126(1): 35‒44.
[17]
Mailach R., Vogeler K., Aerodynamic blade row interactions in an axial compressor—part II: unsteady profile pressure distribution and blade forces. Journal of Turbomachinery, 2004, 126(1): 45‒51.
[18]
Wisler D.C., Core compressor exit stage study. Volume 1: blading design. Fluid system components division, fan and compressor branch, NASA-Lewis Research Center, 1977.
[19]
Wisler D.C., Loss reduction in axial-flow compressors through low-speed model testing. Journal of Engineering for Gas Turbines and Power, 1985, 107(2): 354‒363.
[20]
Lyes P.A., Ginder R.B., Experimental evaluation of the high-to-low speed transformation process for a highly loaded core compressor stage. ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. ASME, 1998. DOI: 10.1115/98-GT-334.
[21]
Lyes P., Low-speed compressor tests of swept and bowed blade designs. International Society for Air Breathing Engines- ISOABE, ISABE- International Symposium on Air Breathing Engines, 14th, Florence, Italy. 1999.
[22]
Gallimore S.J., Bolger J.J., Cumpsty N.A., et al., The use of sweep and dihedral in multistage axial flow compressor blading—Part II: Low and high-speed designs and test verification. Journal of Turbomachinery, 2002, 124(4): 533‒541.
[23]
Wang Z.Q., Research on the method of low-speed model testing for high pressure compressor. Ph.D. thesis, Nanjing University of Aeronautics and Astronautics, Nanjing, China, 2010. (in Chinese)
[24]
Zhang C., Wang Z., Yin C., et al., Low-speed model testing studies for an exit stage of high pressure compressor. Journal of Engineering for Gas Turbines and Power, 2014, 136(11): 112603.
[25]
Zhang C., Hu J., Wang Z., et al., Experimental investigations on three-dimensional blading optimization for low-speed model testing. Journal of Engineering for Gas Turbines and Power, 2016, 138(12): 122602.
[26]
Wang Z., Lu B., Zhang C., et al., Flow field measurement in multi-stage axial compressor stator by using multi-hole pneumatic probes. International Journal of Turbo & Jet-Engines, 2017, 34(1): 81‒94.
[27]
Zhang C., Hu J., Li J., et al., Three-dimensional compressor blading design improvements in low-speed model testing. Aerospace Science and Technology, 2017, 63: 179‒190.
[28]
Wang J., Hu J., Jiang C., et al., Non-axisymmetric shroud profiled endwall optimization of an embedded stator and experimental investigation. Energies, 2020, 13(3): 1‒22.
[29]
Bettner J.L., Experimental investigation in an annular cascade sector of highly loaded turbine stator blading: analysis and design. Vol. 1. National Aeronautics and Space Administration, 1968.
[30]
Wiers S.H., Fransson T.H., Rådeklint U., et al., Flow field measurements in a cold flow annular sector turbine cascade test facility and an annular sector cascade test facility operating at near-engine conditions. ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers Digital Collection, 2001.DOI: 10.1115/2001-GT-0491.
[31]
Vogt D.M., Fransson T.H., A new turbine cascade for aeromechanical testing. 16th Symposium on Measuring Techniques in Transonic and Supersonic Flow in Cascades and Turbomachines, Cambridge, UK, Sept. 2002.
[32]
Saha R., Aerodynamic investigations of a high pressure turbine vane with leading edge contouring at endwall in a transonic annular sector cascade. KTH Royal Institute of Technology, 2012.
[33]
Povey T., Jones T.V., Oldfield M.L., et al., On a novel annular sector cascade technique. Journal of Turbomachinery, 2007, 129(1): 175‒183.
[34]
Villafañe L., Paniagua G., Kaya M., et al., Development of a transonic wind tunnel to investigate engine bypass flow heat exchangers. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2011, 225(8): 902‒914.
[35]
Chen S., Chen F., Feng D., et al., Effects of blade curved on compressor cascades with different camber angles under different incidences. Journal of Aerospace Power, 2007(3): 406‒411. (in Chinese)
[36]
Chen S., Fu C., Zhang X., et al., Experimental and numerical investigation for flow in bowed compressor cascade with large turning angles. Journal of Propulsion Technology, 2008, 29(3): 349‒354. (in Chinese)
[37]
Luo J.H., Sun P., Fu W.G., et al., Influence of the suction action by the guide plates on the periodicity of the flow field in the test piece of a sector-shaped cascade. Journal of Engineering for Thermal Energy & Power, 2018, 33(2): 61‒68. (in Chinese)