Mechanism of affecting the performance and internal flow field of an axial flow subsonic compressor with self-recirculation casing treatment

Abstract

This investigation aims to understand the mechanisms of affecting the axial flow compressor performance and internal flow field with the application of self-recirculation casing treatment. Besides, the potentiality of further enhancing the compressor performance and stability by optimizing the geometric structure of self-recirculation casing treatment is discussed in detail. The results show that self-recirculation casing treatment generates about 7.06, 7.89% stall margin improvements in the experiment and full-annulus unsteady calculation, respectively. Moreover, the compressor total pressure and isentropic efficiency are improved among most of operating points, and the experimental and calculated compressor peak efficiencies are increased by 0.7% and 0.6%, respectively. The comparisons between baseline shroud and self-recirculation casing treatment show that the flow conditions of the compressor rotor inlet upstream are improved well with self-recirculation casing treatment, and the degree of the pressure enhancement in the blade top passage for self-recirculation casing treatment is higher than that for baseline. Further, self-recirculation casing treatment can restrain the leading edge-spilled flows made by the blade tip clearance leakage flows and weaken the blade tip passage blockage. Hence, the flow loss near the rotor top passage is reduced after the application of self-recirculation casing treatment. The rotor performance and stability for self-recirculation casing treatment are greater than those for baseline. The flow-field analyses also indicate that the adverse effects caused by the clearance leakage flows of the blades tip rear are greater than those made by the clearance leakage flows of the blades leading edge. When one injecting part of self-recirculation casing treatment is aligned with the inlet of one blade tip passage, the flow-field quality in the passage is not the best among all the passages between two adjacent injecting parts of self-recirculation casing treatment. Further, the flow-field analyses also indicate that the effect of the relative position between the blade and self-recirculation casing treatment on the flows in the self-recirculation casing treatment may be ignored during the optimization of the recirculating loop configuration.

Keywords

Axial flow rotor performance clearance leakage flow self-recirculation casing treatment flow loss

Get full access to this article

View all access options for this article.

References

Suder

Hathaway

Thorp

, et al. Compressor stability enhancement using discrete tip injection, New York, NY: International Gas Turbine Institute, ASME, 2000.

Leinhos DC and Scheidler S. Active stabilization of a low pressure compressor in a turbofan engine with constant air injection. In: 37th joint propulsion conference and exhibit, Salt Lake City, USA, 8–11 July 2001, AIAA 2001-3312.

Nie

Cheng

, et al. Micro air injection and its unsteady response in a low-speed axial compressor. J Turbomach 2002; 124: 572–579.

Roy B, Chouhan M and Kaundinya KV. Experimental study of boundary layer control through tip injection on straight and swept compressor blades. In: ASME turbo expo 2005: power for land, sea, and air, Reno, Nevada, USA, ASME paper, GT2005-68304.

Beheshti BH, Ghorbanian K, Farhanieh B, et al. A new design for tip injection in transonic axial compressors. In: ASME turbo expo 2006: power for land, sea, and air, Barcelona, Spain, 8–11 May 2006, pp.39–47. New York, NY: ASME.

Kefalakis M and Papailiou KD. Active flow control for increasing the surge margin of an axial flow compressor. ASME Paper, GT-2006-90113, 2006.

Cassina G and Beheshti BH. Parametric study of tip injection in an axial flow compressor stage. In: Proceedings of ASME turbo expo 2007, GT2007-27403, 2007.

Horn W and Schmidt K-J. Effects of compressor tip injection on aircraft engine performance and stability. In: Proceedings of ASME turbo expo 2007, GT2007-27574, 2007.

Hiller S-J and Matzgeller R. Stability enhancement of a multi stage compressor by air injection. In: Proceedings of ASME turbo expo 2009, GT2009-59868, 2009.

10.

Matzgeller R, Voges M and Schroll M. Investigation of unsteady compressor flow structure with tip injection using particle image velocimetry. In: Proceedings of ASME turbo expo 2011, GT2011-45281, 2011.

11.

Cong-Truong

Man-Woong

Kwang-Yong

. Aerodynamic performance of transonic axial compressor with a casing groove combined with blade tip injection and ejection. Aerosp Sci Technol 2015; 46: 176–187.

12.

Hossein

Mohammad-Amin

Abolghasem

. Role of tip injection in desensitizing the compressor to the tip clearance size. Aerosp Sci Technol 2016; 82: 10–17.

13.

Taghavi-Zenouz

Hosein

ABM

. Improvement of aerodynamic performance of a low speed axial compressor rotor blade row through air injection. Aerosp Sci Technol 2018; 72: 409–417.

14.

Michael

. Self-recirculating casing treatment concept for enhanced compressor performance, New York, NY: ASME, 2002, pp. 1–10.

15.

Yang H, Nuernberger D, Nicke E, et al. Numerical investigation of casing treatment mechanisms with a conservative mixed-cell approach. In: ASME turbo expo 2003, collocated with the 2003 international joint power generation conference, Atlanta, Georgia, 16–19 June 2003, pp.961–974. New York, NY: ASME.

16.

Strazisar AJ, Bright MM, Thorp S, et al. Compressor stall control through end-wall recirculation. In: ASME Turbo Expo 2004, GT2004-54295, 2004.

17.

Fite EB. Fan performance from duct rake instrumentation on a 1.294 pressure ratio, 725 ft/sec tip speed turbofan simulator using vaned passage casing treatment. Cleveland, OH, NASA/TM – 2006-214241, 2006.

18.

Dobrzynski

Saathoff

Kosyna

. Active flow control in a single-stage axial compressor using tip injection and endwall boundary layer removal, New York, NY: ASME, 2008, pp. 1–10.

19.

Weichert S, Day I and Freeman C. Self-regulating casing treatment for axial compressor stability enhancement. In: Proceedings of the ASME turbo expo 2011, Gt2011-46042, 2011.

20.

Khaleghi

. Effect of discrete endwall recirculation on the stability of a high-speed compressor rotor. Aerosp Sci Technol 2014; 37: 130–113.

21.

Lin

Liu

, et al. Experimental investigation of self-recirculating tip air injection in transonic axial flow compressor. J Mech Eng 2014; 50: 135–143.

22.

Yang

Zhao

, et al. Investigation on multiple cylindrical holes casing treatment for transonic axial compressor stability enhancement. J Therm Sci 2014; 23: 346–353.

23.

Wang

Chu

Zhang

. Mechanism study of performance enhancement in a subsonic axial flow compressor with recirculating casing treatment. Proc IMechE, Part G: J Aerospace Engineering 2018; 232: 680–693.

24.

Lu X, Chu W, Zhu J, et al. Experimental and numerical investigation of a subsonic compressor with bend skewed slots casing treatment. ASME Paper, GT-2006-90026.

25.

Zhang HG, Tan F, Wu YH, et al. Experimental and numerical investigation of effect of center offset degree on compressor stability with circumferential grooved casing treatment. Report no. ASME GT-56757, 2016. Seoul, South Korea: ASME. Turbo Expo: Power for Land, Sea, and Air.

26.

Zhang

, et al. Flow mechanism of affecting an axial flow compressor performance and stability with cross-blade slot casing treatments. Proc IMechE, Part A: J Power and Energy 2019; 233: 17–36.

27.

Zhang

Liu

Wang

, et al. Mechanism investigation of enhancing the stability of an axial flow rotor by blade angle slots. Proc IMechE, Part G: J Aerospace Engineering 2019; 233: 4750–4764.

28.

Zhang

Wang

, et al. Mechanism of affecting the axial rotor stability and performance with center offset degrees of axial skewed slots. Proc IMechE, Part G: J Aerospace Engineering 2020; 234: 330–341.