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 哈尔滨工程大学学报  2019, Vol. 40 Issue (5): 938-943  DOI: 10.11990/jheu.201803099 0

### 引用本文

TIAN Zhitao, ZHENG Qun, JIANG Bin, et al. Investigation on the tip clearance structure of a helium compressor rotor[J]. Journal of Harbin Engineering University, 2019, 40(5), 938-943. DOI: 10.11990/jheu.201803099.

### 文章历史

Investigation on the tip clearance structure of a helium compressor rotor
TIAN Zhitao , ZHENG Qun , JIANG Bin , ZHAO Wenfeng , DUAN Yu
College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China
Abstract: The highly loaded design method of helium compressors can effectively solve the compression problem arising from the use of helium in high-temperature gas-cooled reactors. However, it also leads to more leakage problems at the tip clearance of a highly loaded helium compressor. In this paper, the numerical simulation is used to study the formation mechanism of the tip clearance leakage vortex of a helium compressor rotor, the control mechanism of the rotor upper end wall gap structure, and its control function on the tip clearance leakage vortex. Results showed that the unilateral groove on the leading edge of the rotor tip of the helium compressor has the most obvious control effect on the tip clearance leakage loss, and the performance improvement of the helium compressor rotor is the greatest when the groove measures 30°. In addition, the greater the clearance, the stronger the effectiveness of the unilateral groove. Finally, when the tip clearance is 1 mm, the adiabatic efficiency of the compressor rotor increased by 0.15%. The single side slot on the tip clearance of the helium compressor rotor can effectively control tip clearance leakage loss and improve compressor performance at design point.
Keywords: helium compressor    high load design    numerical simulation    unilateral groove    tip clearance leakage    clearance structure    adiabatic efficiency

1 计算数值模型

 Download: 图 2 不同网格节点的计算结果 Fig. 2 Numerical results with different grid points

2 压气机转子上端壁结构形式对叶顶泄漏的影响 2.1 转子上端壁槽的形式对叶顶泄漏的影响

 Download: 图 4 研究的叶顶示意 Fig. 4 Representation of the tip topologies under investigation

3种不同叶顶结构形式的氦压缩机绝热效率计算结果分别为0.925 72、0.926 75及0.925 59。叶顶前缘单侧槽结构形式相比与平顶结构和前缘与尾缘双侧槽结构氦压缩机具有最高的效率，初步认为这是由槽结构减少叶顶泄漏损失与槽结构本身的附加损失2方面因素共同作用的结果。

 ${C_{\rm{P}}} = \left( {p - {p_{{\rm{in}}}}} \right)/\left( {{p_{{\rm{t}}{\rm{.in}}}} - {p_{{\rm{in}}}}} \right)$ (1)
 Download: 图 5 98%叶高处的表面静压系数分布 Fig. 5 Static pressure coefficient distributions of rotor at 98% height

 Download: 图 6 前缘单侧槽作用机理 Fig. 6 Action mechanism of unilateral groove clearance

 Download: 图 7 上端壁表面静压分布 Fig. 7 Contour of shroud surface pressure distribution
2.2 叶顶前缘槽的角度对叶顶泄漏的影响

 Download: 图 9 不同坡度98%叶高处静压系数分布 Fig. 9 Static pressure coefficient distributions of rotor at 98% height for different slopes

 $\omega = \frac{{{p_{{\rm{t}}{\rm{.in}}}} - {p_{\rm{t}}}}}{{{p_{{\rm{t}}{\rm{.in}}}} - {p_{{\rm{in}}}}}}$ (2)
 Download: 图 10 压气机动叶上端壁总压损失系数分布 Fig. 10 Contour of shroud surface total pressure loss coefficient distribution

 Download: 图 11 压气机总压损失系数沿轴向的分布 Fig. 11 The distribution of the total pressure loss coefficient along the axial direction

2.3 叶顶前缘槽对不同叶顶间隙的氦压球机的性能的影响

 Download: 图 13 压气机转子上端壁总压损失系数分布 Fig. 13 Contour of shroud surface total pressure loss coefficient distribution