LI Xinlong
,
LIU Shuaipeng
,
GENG Shaojuan
,
ZHANG Hongwu
. Influence of Hub Contouring on the Performance of a Transonic Axial Compressor Stage with Low Hub-Tip Ratio[J]. 热科学学报, 2022
, 31(1)
: 179
-188
.
DOI: 10.1007/s11630-022-1522-6
The rotor blade height with low hub-tip ratio is relatively longer, and the aerodynamic parameters change drastically from hub to tip. Especially the organization of flow field at hub becomes more difficult. This paper takes a transonic 1.5-stage axial compressor with low hub-tip ratio as the research object. The influence of four types of rotor hub contouring on the performance of transonic rotor and stage is explored through numerical simulation. The three-dimensional numerical simulation results show that different hub contourings have obvious influence on the flow field of transonic compressor rotor and stage, thus affecting the compressor performance. The detailed comparison is conducted at the rotor peak efficiency point for each hub contouring. Compared with the linear hub contouring, the concave hub contouring can improve the flow capacity, improve the rotor working capacity, and increase the flow rate. The flow field near blade root and efficiency of transonic rotor is improved. The convex hub contouring will reduce the mass flow rate, pressure ratio and efficiency of the transonic rotor. Full consideration should be given to the influence of stator flow field by hub contouring.
[1] LeJambre C.R., Zacharias R.M., Biederman B.P., Gleixner A.J., Yetka C.J., Development and application of a multistage Navier-Stokes flow solver: Part II- Application to a high-pressure compressor design. ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. Houston, Texas, USA, Turbomachinery 1995, 1: V001T01A093. DOI: 10.1115/1.2841395.
[2] Stringham G.D., Cassem B.N., Prince T.C., Yeung P.F., Design and development of a nine stage axial flow compressor for industrial gas turbines. ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. Stockholm, Sweden, Turbomachinery. 1998, (1): V001T01A042. DOI: 0.1115/98-GT-140.
[3] Hoeger M., Cardamone P., Fotter L., Influence of endwall contouring on the transonic flow in a compressor blade. ASME Turbo Expo 2002: Power for Land, Sea, and Air. The Netherlands, Turbo Expo 2002, Parts A and B. Amsterdam, 2002, (5): 759–768.
DOI: 10.1115/GT2002-30440
[4] Huang S., Yang C., Li Z., Han G., Lu X., Effect of non-axisymmetric end wall on a highly loaded compressor cascade in multi-conditions. Journal of Thermal Science, 2021, 30: 1363–1375.
[5] Xu Q.Y., Hou A.P., Li S.W., Zhou S., Influences of hub design on rotor performance in transonic compressor. Journal of Engineering Thermophysics, 2009, 30: 761–764.
[6] Yang C., Li Q.S, Cui J., Zhang M.M., Zhou S., The application of aero rule in the improvement design of meridian shape. Journal of Engineering Thermophysics, 2007, 02: 226–228.
[7] Cui J., Cheng Z., Yang C., Liu Y., Zhou S., Blockage area rule for multi-stage axial compressor meridional channel. Journal of Aerospace Power, 2010, 11: 2520–2527.
[8] Li Z., Zhang Y., Pan T., Lu, H., Wu, M., Zhang, J., Optimization strategy for a single-stage axisymmetric hub endwall in axial compressor by a modified transonic area rule. Aerospace Science and Technology, 2018, 82–83(Nov): 199–209.
[9] Sun S.J., Chen S.W., Liu W., Gong Y., Wang S.T., Effect of axisymmetric endwall contouring on the high-load low-reaction transonic compressor rotor with a substantial meridian contraction. Aerospace Science and Technology, 2018, 81: 78–87.
[10] Lu D.J., Connection and continuity of the Bezier curve. Journal of Qinghai University, 2004, 22: 84–86.
[11] Reid L., Moore R.D., 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 1.82. NASA Technical Report, Report No. TP1338, 1978.
[12] Reid L., Moore R.D., Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor. NASA Technical Report, Report No. TP1337, 1978.
[13] Lu X.G., Study on internal flow instability of axial compressor and its passive control strategy. Northwestern Polytechnical University, Xi’an, China, 2007.
[14] Geng S.J., Numerical investigation on the unsteady response of compressor tip leakage flow to discrete micro tip injection and its effect on stability enhancement. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China, 2007.
