Influence of elliptical casing deformation on aerodynamic loss performance of subsonic compressor rotor
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摘要:
选用某亚声速轴流压气机，借助经过校核的数值计算方法深入开展了53%设计转速下压气机机匣椭圆变形的典型流动特征和损失特性辨析。结果表明：随着机匣变形度的增加，压气机叶顶区域流动和损失恶化，压气机气动效率加速下降且峰值效率最高降低2.1%。机匣椭圆变形下压气机叶顶流动恶化源于转子上游流场周向畸变及其新增流动损失：叶顶间隙周向不均匀导致转子最大叶顶间隙通道的上游压力势场畸变，形成顺叶片旋转方向的压力梯度和周向二次流动，诱发低能流体向偏离最大叶顶间隙的周向位置迁移堆积并形成高损失区，损失周向分布出现“相位偏移”现象。相对机匣变形下转子叶顶间隙变化导致泄漏损失增加，转子上游损失畸变对转子内部叶顶损失影响更为深远，其一方面决定了转子内损失峰值所在的叶片通道，另一方面在转子内发展演化诱发了更大间隙泄漏损失。
Abstract:Focusing on a subsonic axial-flow compressor, the typical flow characteristics and loss characteristics of a subsonic axial-flow compressor with elliptical deformation of the casing were investigated by means of a calibrated numerical method at 53% design speed. The results indicated that the flow and loss in the tip region of the compressor blade were deteriorated as the deformation degree of the casing increased, and the aerodynamic efficiency of the compressor decreased more sharply with a peak efficiency decrease of up to 2.1%. The deterioration of tip flow under casing deformation was due to circumferential distortion of the upstream flow field of the rotor and its induced flow losses: the uneven circumferential clearance at the blade tip led to distortion of the upstream pressure potential field in the maximum blade tip clearance channel of the rotor, forming a pressure gradient and circumferential secondary flow in the direction of blade rotation, inducing low-energy fluid to migrate and accumulate towards the circumferential position deviating from the maximum blade tip clearance and forming a high loss region. The loss circumferential distribution exhibited a “phase shift” phenomenon. Compared with the change in rotor tip clearance under casing deformation which led to an increase in leakage loss, the upstream loss distortion of the rotor had a more profound impact on the internal tip loss of the rotor. On the one hand, it determined which blade channel the peak loss region lied in, and on the other hand, the development and evolution within the rotor induced larger tip leakage loss.
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Key words:
- axial compressor /
- casing deformation /
- uneven tip clearance /
- flow mechanism /
- loss characteristic
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图 1 机匣变形下压气机叶顶间隙周向分布示意图
Figure 1. Illustration of circumferential tip clearance distribution in a compressor with casing deformation
图 2 不同机匣变形度下叶顶间隙在周向上的分布
Figure 2. Circumferential distribution of the tip clearance with different casing deformation degrees
图 4 原型机匣下压气机气动特性（转速为
8130 r/min）Figure 4. Aerodynamic performance of the compressor with original casing （speed of
8130 r/min）
图 5 不同机匣变形度下压气机气动特性对比
Figure 5. Comparison of the compressor aerodynamic performance with different casing deformation degrees
图 6 不同机匣变形度下压气机峰值效率变化
Figure 6. Variation of the compressor peak efficiency with different casing deformation degrees
图 7 不同机匣变形度下叶顶熵值沿周向分布对比
Figure 7. Circumferential distribution comparison of the entropy of tip region with different casing deformation degrees
图 8 不同机匣变形度下转子叶片上游流动损失发展演化对比
Figure 8. Comparison of rotor upstream loss development with different casing deformation degrees
图 9 不同机匣变形度下转子叶片上游的流向涡与流动损失对比
Figure 9. Comparison of rotor upstream vortex and loss with different casing deformation degrees
图 10 不同机匣变形度下转子叶片上游静压势场分布对比
Figure 10. Comparison of rotor upstream static pressure distribution with different casing deformation degrees
图 11 不同机匣变形度下转子叶片进口通流能力对比
Figure 11. Comparison of rotor upstream mass flow distribution with different casing deformation degrees
图 12 不同机匣变形度下转子叶片通道内部流动损失发展演化对比
Figure 12. Comparison of flow loss development within the blade passages with different casing deformation degrees
图 13 机匣变形度τ=0和τ=0.9时不同转子叶片通道流动损失变化
Figure 13. Changes in flow loss characteristics of different rotor blade passages with casing deformation degrees τ=0 and τ=0.9
图 14 机匣变形下叶顶载荷周向分布对比（98%叶高）
Figure 14. Circumferential distribution comparison of the blade tip loading for casing deformation cases （98% span）
图 15 机匣变形下不同周向位置叶顶进口相对气流角分布对比（98%叶高）
Figure 15. Distribution comparison of the blade tip inlet relative flow angle at different circumferential locations for casing deformation cases （98% span）
表 1 压气机的主要设计参数
Table 1. Main design parameters of compressor
参数 数值 设计质量流量/（kg/s） 5.6 压比 1.25 效率 0.905 设计转速/（r/min） 15200 机匣直径/mm 298 叶顶间隙/mm 0.5 叶顶进口马赫数 0.78 轮毂比 0.61 叶片数 30 
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