[1] K. Yamada, H. Kikuta, K.-i. Iwakiri, M. Furukawa, and S. Gunjishima. (2013) An explanation for flow features of spike-type stall inception in an axial compressor rotor. J. Turbomach. vol. 135.

[4] C.-T. Dinh, M.-W. Heo, and K.-Y. Kim. (2015) Aerodynamic performance of transonic axial compressor with a casing groove combined with blade tip injection and ejection. Aerosp Sci Technol. vol. 46, pp. 176-187.

[5] S. Abbasi, A. Pirnia, and R. Taghavi-Zenouz. (2018) Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method. JTAM. vol. 56, pp. 1005-1015..

[6] S. Abbasi and A. Joodaki. (2020) Effect of blade profile on the performance characteristics of axial compressor in design condition. JCARME. vol. 9, pp. 287-296.

[7] S. Abbasi and A. Gholamalipour. (2020) Parametric study of injection from the casing in an axial turbine. P I MECH ENG A-J POW. vol. 234, pp. 582-593.

[9]  ش. فرد, ر. اسلامی و زارع. (1395) تحلیل فرکانسی ریزش گردابه در کسکید کمپرسور محوری در اعداد رینولدز متوسط. مکانیک سازه ها و شاره ها.

[10] H. Chen, X. Huang, K. Shi, S. Fu, M. Ross, M. A. Bennington, et al.(2014) A computational fluid dynamics study of circumferential groove casing treatment in a transonic axial compressor. J. Turbomach. vol. 136.

[11] C. Hah.(2017) Effects of double-leakage tip clearance flow on the performance of a compressor stage with a large rotor tip gap. J. Turbomach. vol. 139.

[12] X. Ren and C. Gu.(2016) A numerical study on the tip clearance in an axial transonic compressor rotor. Appl. Therm. Eng. vol. 103, pp. 282-290.

[13] D. Wisler.(1984) Loss reduction in axial-flow compressors through low-speed model testing. ASME paper p. 184.

[14] M. W. Wiseman and T.-H. Guo (2001) An investigation of life extending control techniques for gas turbine engines. ACC (Cat. No. 01CH37148)  pp. 3706-3707.

[15] I. Wilke, H.-P. Kau, and G. Brignole (2005) Numerically aided design of a high-efficient casing treatment for a transonic compressor in Turbo Expo. JPLCA pp. 353-364.

[16] R. Davis and J. Yao (2006) Axial compressor rotor flow structure at stall-inception. in 44th AIAA ASME. p. 419.

[17] M. Zhang and A. Hou. (2017) Investigation on stall inception of axial compressor under inlet rotating distortion. P I MECH ENG A-J Mech. Eng. Sci.. vol. 231, pp. 1859-1870.

[18] J. J. Adamczyk, M. Celestina, and E. Greitzer. (1993) The role of tip clearance in high-speed fan stall. ASME 345 E.47.

[19] I. Wilke and H.-P. Kau (2003) A numerical investigation of the flow mechanisms in a HPC front stage with axial slots. Turbo Expo PLSA.  pp. 465-477.

[20] A. Epstein, J. F. Williams, and E. Greitzer. (1989) Active suppression of aerodynamic instabilities in turbomachines. Propuls. Power.  vol. 5, pp. 204-211.

[21] R. Taghavi-Zenouz and S. Abbasi. (2015) Alleviation of spike stall in axial compressors utilizing grooved casing treatment. CJA. vol. 28, pp. 649-658.

[22] T.-D. Vuong, K.-Y. Kim, and C.-T. Dinh. (2021) Recirculation-groove coupled casing treatment for a transonic axial compressor. Aerosp. Sci. Technol. vol. 111, p. 106556.

[23] C. Nie, Z. Tong, S. Geng, J. Zhu, and W. Huang. (2007) Experimental investigations of micro air injection to control rotating stall. J. Therm. Sci. vol. 16, pp. 1-6.

[24] K. L. Suder, M. D. Hathaway, S. A. Thorp, A. J. Strazisar, and M. B. Bright. (2001) Compressor stability enhancement using discrete tip injection. J. Turbomach. vol. 123, pp. 14-23.

[25] H. Khaleghi. (2014) Effect of discrete endwall recirculation on the stability of a high-speed compressor rotor. Aerosp. Sci. Technol. vol. 37, pp. 130-1370.

[26] G. Cassina, B. H. Beheshti, A. Kammerer, and R. S. Abhari (2007) Parametric study of tip injection in an axial flow compressor stage. Turbo Expo. PLSA. pp. 137-145.

[27] J. Li. (2017) Self-adaptive stability-enhancing technology with tip air injection in an axial flow compressor. J. Turbomach vol. 139.

[28] J. Li, F. Lin, Z. Tong, C. Nie, and J. Chen. (2015) The dual mechanisms and implementations of stability enhancement with discrete tip injection in axial flow compressors. J. Turbomach. vol. 137.

[29] J. Li, J. Du, Z. Li, and F. Lin. (2018) Stability enhancement with self-recirculating injection in axial flow compressor. J. Turbomach. vol. 140.

[30] I. Benhegouga and Y. Ce. (2013) Steady Air Injection Flow Control Parameters in a Transonic Axial Compressor. Res. J. Appl. Sci. vol. 5, pp. 1441-1448.

[31] X. Liu, J. Teng, J. Yang, X. Sun, D. Sun, C. He, et al. (2019) Calculation of stall margin enhancement with micro-tip injection in an axial compressor. J. Fluids Eng. vol. 141.

[32] W. Wei, C. Wuli, H. Zhang, and H. Kuang. (2017) Experimental and numerical study of tip injection in a subsonic axial flow compressor. CJA. vol. 30, pp. 907-917.

[33] B. Beheshti, B. Farhanieh, K. Ghorbanian, J. Teixeira, and P. Ivey. (2005) Performance enhancement in transonic axial compressors using blade tip injection coupled with casing treatment. Proc. Inst. Mech. Eng. A: J. Power Energy.  vol. 219, pp. 321-331.

[34] B. H. Beheshti, K. Ghorbanian, B. Farhanieh, J. A. Teixeira, and P. C. Ivey (2006) A new design for tip injection in transonic axial compressors. Turbo Expo. PLSA. pp. 39-47.

[35] K. L. Suder, M. D. Hathaway, S. A. Thorp, A. J. Strazisar, and M. B. Bright (2000) Compressor stability enhancement using discrete tip injection. Turbo Expo. PLSA. p. V001T03A110.

[36] A. Mushtaq, K. Parvez, S. Ahmad, and J. Khan (2011) Parametric Study of Tip Injection on Stability of Transonic Axial Flow Compressor. in 49th AIAA ASM. 2011, p. 744.

[37] X. Lu, W. Chu, J. Zhu, and Z. Tong. (2006) Numerical and experimental investigations of steady micro-tip injection on a subsonic axial-flow compressor rotor. Int. J. Rotating Mach. vol. 2006.

[38] B. H. Beheshti, K. Ghorbanian, B. Farhanieh, J. A. Teixeira, and P. C. Ivey (2006) A new design for tip injection in transonic axial compressors. Turbo Expo. PLSA. pp.39-47.

[39] N. Ahmad, J. Bin, Z. Qun, S. A. Ahmad, and H. Fawzy. (2020) Performance enhancement of a transonic axial flow compressor with circumferential casing grooves to improve the stall margin. J. Appl. Fluid Mech. vol. 13, pp. 221-232.

[40] J. Li, J. Du, S. Geng, F. Li, and H. Zhang. (2020) Tip air injection to extend stall margin of multi-stage axial flow compressor with inlet radial distortion. Aerosp. Sci. Technol. vol. 96, p. 105554.

[41] J. Li. (2017) Self-adaptive stability-enhancing technology with tip air injection in an axial flow compressor. J. Turbomach. vol. 139, p. 011008.

[42] R. D. Moore (1980) Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05. NASA.

[43] L. Reid and R. D. Moore. (1978) Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor. TP, Doc. ID. 19780025165.

[44] D. Anderson, J. C. Tannehill, and R. H. Pletcher (2016) Computational fluid mechanics and heat transfer: Taylor and Francis. 3th edn.  Taylor and Francis.

 

[45] T. Cebeci and A. Smith. (1974) Analysis of Turbulent Boundary Layers. New York; San Francisco, London, Academic Press.

[46] M. D. Hathaway (2002) Self-recirculating casing treatment concept for enhanced compressor performance. NASA/TM-211569 vol. 3610.