Multistage axial compressor is one of the key components in aero engines and gas turbines. In this paper, a five-stage axial compressor was studied to improve the efficiency. First, the loss analyses of the datum compressor were performed. The results showed that front rotors and rear stators have higher loss. Based on the loss analyses, the corresponding flow controls were introduced. The endwall treatment was performed with the rear stators, S3, S4, and S5, by end-bow, which changed the blade loading and reduced the loss due to endwall boundary layer. The efficiency of the datum compressor was increased by 0.5%. Based on the improved redesign of rear stators, shock control was introduced to front rotors, R1 and R2, characterized by sweep, which changed the shock structure and decreased the shock-induced loss and shock-tip leakage interaction. Coupled between endwall treatment and shock control, compared to the datum compressor, the efficiency, peak pressure ratio, and choked mass flow were increased by 1.1%, 1.1%, and 1.2%, respectively. At off-design speeds, the performances were also improved, which implies the flow controls for design speed remain effective in a range of off-design speeds. The reliability of the redesigned compressor was validated by stress and mode analyses.
DentonJD. The 1993 IGTI Scholar Lecture: Loss mechanisms in turbomachines. J Turbomach1993; 115: 621–656.
2.
WislerDC. Loss reduction in axial-flow compressors through low-speed model testing. J Eng Gas Turbines Power1985; 107: 354–363.
3.
PratoJLakshminarayanaBSuryavamshiN. Three-dimensional flow field downstream of an embedded stator in a multistage axial flow compressor: part I: Steady and unsteady flow fields. Proc IMechE, Part A: J Power and Energy2001; 215: 281–299.
4.
CumpstyNA. Annulus wall boundary layer measurements in a four-stage compressor. J Eng Gas Turbines Power1986; 108: 2–6.
5.
GourdainNStollMMontagnacM, et al.Numerical investigation of the tip leakage flow in a multistage high pressure compressor. Comput Fluid Dyn2009, pp. 217–229.
6.
BerdanierRAKeyNL. The effects of tip leakage flow on the performance of multistage compressors used in small core engine applications. J Eng Gas Turbines Power2015; 138: 052605–052605.
7.
BerdanierRAKeyNL. Experimental characterization of tip leakage flow trajectories in a multistage compressor. J Propul Power2016; 32: 1022–1032.
8.
DomercqOEscuretJF. Tip clearance effect on high-pressure compressor stage matching. Proc IMechE, Part A: J Power and Energy2007; 221: 759–767.
9.
YangDZhengXQLiQS. An 11-stage axial compressor performance simulation considering the change of tip clearance in different operating conditions. Proc IMechE, Part A: J Power and Energy2014; 228: 614–625.
10.
Zheng XQ and Yang HL. Influence of tip clearance on the performance and matching of multistage axial compressors. In: Proceeding of ASME Turbo Expo, 2016, Seoul, South Korea, 13–17 June 2016, paper no. GT2016-56232.
11.
AtkinCJSquireLC. A study of the interaction of a normal shock wave with a turbulent boundary layer at Mach numbers between 1.30 and 1.55. Euro J Mech B/Fluids1992; 11: 93–118.
12.
Hofmann W and Ballmann J. Tip clearance vortex development and shock-vortex-interaction in a transonic axial compressor rotor. In: Proceedings of AIAA aerospace sciences meeting & exhibit, 2002, Reno, NV, USA, 14–17 January 2002, paper no. AIAA 2002-0083.
13.
PuterbaughSLBrendelM. Tip clearance flow-shock interaction in a transonic compressor rotor. J Propul Power1997; 13: 24–30.
14.
BiolloRBeniniE. Shock/boundary layer/tip clearance interaction in a transonic rotor blade. J Propul Power2009; 25: 668–677.
BeniniEBiolloR. Aerodynamics of swept and leaned transonic compressor rotors. Appl Energy2007; 84: 1012–1027.
17.
Müller MW, Biela C, Schiffer H-P, et al. Interaction of rotor and casing treatment flow in an axial single-stage transonic compressor with circumferential grooves. In: Proceedings of ASME turbo expo, 2008, Berlin, Germany, 9–13 June 2008, paper no. GT2008-50135.
18.
ZhengXQZhouXBZhouS. Investigation on a type of flow control to weaken unsteady separated flows by unsteady excitation in axial flow compressors. J Turbomach2005; 127: 489–496.
19.
ZhengXQZhangYJXingWD, et al.Separation control of axial compressor cascade by fluidic-based excitations. J Turbomach2011; 133: 041016–041016.
20.
ZhengXQZhouSLuYJ, et al.Flow control of annular compressor cascade by synthetic jets. J Turbomach2008; 130: 021018–021018.
21.
Wang ZQ, Lai SK and Xu WY. Aerodynamic calculation of turbine stator cascades with curvilinear leaned blades and some experimental results. In: Proceedings of international symposium on air breathing engines, Bangalore, India, 16–22 February 1981, pp.1–9.
22.
Weingold HD, Neubert RJ, Behlke RF, et al. Reduction of compressor stator endwall losses through the use of bowed stators. In: Proceedings of ASME turbo expo, 1995, Houston, TX, USA, 5–8 June 1995, paper no. 95-GT-380.
23.
FreemanC. Effect of tip clearance flow on compressor stability and engine performance. VKI Lecture Series 1985-05 on Tip Clearance in Axial Turbomachines1985, pp. 5–5.
24.
WangSTDuXWangZQ. Study on the effects of end-bend cantilevered stator in a 2-stage axial compressor. J Therm Sci2009; 18: 119–125.
25.
LiZHZhengXQLiuYM, et al.The effect of end wall boundary layer on matching and corresponding flow control technique for multistage axial compressor. Proc IMechE, Part G: J Aerospace Engineering2016; 230: 2179–2194.
26.
DentonJDXuL. The exploitation of three-dimensional flow in turbomachinery design. Proc IMechE, Part C: J Mechanical Engineering Science1998; 213: 125–137.
27.
PassruckerHEngberMKablitzS, et al.Effect of forward sweep in a transonic compressor rotor. Proc IMechE, Part A: J Power Energy2003; 217: 357–365.
28.
Bergner J, Kablitz S, Hennecke D, et al. Influence of sweep on the 3D shock structure in an axial transonic compressor. In: Proceedings of ASME turbo expo, 2005, Reno, NV, USA, 6–9 June 2005, paper no. GT2005-68835.
29.
Yamaguchi N, Tominaga T, Hattori S, et al. Secondary-loss reduction by forward-skewing of axial compressor rotor blading. In: Proceedings of 1991 Yokohama international gas turbine congress, 1991, pp.61–68.
30.
OkuiHVerstraeteTVan den BraembusscheRA, et al.Three-dimensional design and optimization of a transonic rotor in axial flow compressors. J Turbomach2013; 135: 031009–031009.
31.
GallimoreSJBolgerJJCumpstyNA, et al.The use of sweep and dihedral in multistage axial flow compressor blading - Part I: University research and methods development. J Turbomach2002; 124: 521–532.
32.
GallimoreSJBolgerJJCumpstyNA, et al.The use of sweep and dihedral in multistage axial flow compressor blading - Part II: Low and high-speed designs and test verification. J Turbomach2002; 124: 533–541.
RoachePJ. Quantification of uncertainty in computational fluid dynamics. Annu Rev Fluid Mech1997; 29: 123–160.
35.
ZhengXQYangHL. End-wall boundary layers and blockages of multistage axial compressors under different conditions. J Propul Power2017; 33: 908–916.
36.
ZhengXQLiZH. Blade-end treatment to improve the performance of axial compressors: An overview. Prog Aerosp Sci2017; 88: 1–14.
37.
MirzabozorgMASBazazzadehMHamzezadeM. Numerical study on the effect of single shallow circumferential groove casing treatment on the flow field and the stability of a transonic compressor. J Appl Fluid Mech2017; 10: 257–265.
