Study on combustion flow field characteristics of integrated afterburner with non-uniform inflow
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摘要:
当真实加力燃烧室处于强瞬变过渡态时，复杂的进气来流会使燃烧流场偏离设计点，燃烧性能变差。为了研究非均匀进气来流条件对加力燃烧室燃烧流场的影响规律，针对速度不均匀和余旋角不均匀两种典型进气来流条件下的一体化加力燃烧室流场进行数值模拟。结果表明：随着速度不均匀度的增加，一体化加力燃烧室流场速度梯度沿径向增大，燃烧流场中化学反应核心区面积减小，高温区尺寸减小，燃烧性能变差；随着余旋角不均匀度的增加，冷态流场支板间通道涡结构逐渐增大，涡强度逐渐增强，燃烧流场中化学反应速率增加，高温区尺寸增大，并且沿径向向流场中心偏移，燃烧性能变好；随着不均匀度的增加，一体化加力燃烧室的流阻系数逐渐上升，总压恢复系数逐渐下降，流阻损失增加。
Abstract:When the real afterburner operated in a fast transient transition state, the complex incoming flow caused the flow field to deviate from the design points, resulting in a poor combustion performance. In order to study the influence of non-uniform inflow on the combustion flow field characteristics of an afterburner, the flow field of an integrated afterburners with non-uniform velocity inflow and non-uniform cosine rotation angle inflow was studied numerically. The results showed that: with the increase of non-uniform inlet velocity, the velocity gradient in the integrated afterburner flow field increased radially. In the combustion flow field, the chemical reaction core zone and the high-temperature zone shrank, indicating the combustion performance became worse; With the increase of non-uniform inlet cosine rotation angle, the vortex structure between the struts expanded while the vortex intensity strengthened gradually. In the combustion flow field, the chemical reaction rate increased. The high-temperature zone became larger and shifted towards the center of the flow field radially which indicated a superior combustion performance; with the increase of inflow non-uniformity, the flow resistance loss coefficient of the integrated afterburner increased while the total pressure recovery coefficient declined, showing the increment of the flow resistance loss.
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图 3 一体化加力燃烧室进口速度不均匀分布图
Figure 3. Profile of non-uniform inlet velocity in integrated afterburner
图 4 一体化加力燃烧室进口余旋角不均匀分布图
Figure 4. Profile of non-uniform inlet cosine rotation angle in integrated afterburner
图 5 试验件支板间中心截面速度云图与矢量图
Figure 5. Velocity contour and vectorgraph of the test sample in the central section between the struts
图 6 试验件沿程静压分布
Figure 6. Static pressure distribution of the test sample along the flow direction
图 7 试验件沿程速度分布
Figure 7. Velocity distribution of the test sample along the flow direction
图 9 速度不均匀进气来流条件下冷态流场S1截面速度云图与流线图
Figure 9. Velocity contour and streamline of cold flow field with non-uniform velocity inflow at S1 section
图 10 速度不均匀进气来流条件下冷态流场S1截面回流区
Figure 10. Recirculation zone of cold flow field with non-uniform velocity inflow at S1 section
图 11 速度不均匀进气来流条件下燃烧流场S2截面速度云图与流线图
Figure 11. Velocity contour and streamline of combustion flow field with non-uniform velocity inflow at S2 section
图 12 速度不均匀进气来流条件下燃烧流场S2截面C12H23总包反应化学反应速率云图
Figure 12. Overall chemical reaction rate of C12H23 contour of combustion flow field with non-uniform velocity inflow at S2 section
图 13 速度不均匀进气来流条件下燃烧流场S1截面温度云图
Figure 13. Temperature contour of combustion flow field with non-uniform velocity inflow at S1 section
图 14 速度不均匀进气来流条件下燃烧流场T=
2100 K等温线Figure 14. T=
2100 K isotherm of combustion flow field with non-uniform velocity inflow
图 15 速度不均匀进气来流条件下一体化加力燃烧室流场流阻特性
Figure 15. Flow resistance characteristics of integrated afterburner flow field with non-uniform velocity inflow
图 16 余旋角不均匀进气来流条件下冷态流场S1截面速度云图与流线图
Figure 16. Velocity contour and streamline of cold flow field with non-uniform cosine rotation angle inflow at S1 section
图 17 余旋角不均匀进气来流条件下冷态流场支板间通道涡结构
Figure 17. Vortex structures between the struts in cold flow field with non-uniform cosine rotation angle inflow
图 18 余旋角不均匀进气来流条件下燃烧流场S2截面速度云图与流线图
Figure 18. Velocity contour and streamline of combustion flow field with non-uniform cosine rotation angle inflow at S2 section
图 19 余旋角不均匀进气来流条件下燃烧流场S2截面C12H23总包反应化学反应速率云图
Figure 19. Overall chemical reaction rate of C12H23 contour of combustion flow field with non-uniform cosine rotation angle inflow at S2 section
图 20 余旋角不均匀进气来流条件下燃烧流场S1截面温度云图
Figure 20. Temperature contour of combustion flow field with non-uniform cosine rotation angle inflow at S1 section
图 21 余旋角不均匀进气来流条件下燃烧流场T=
2100 K等温线Figure 21. T=
2100 K isotherm of combustion flow field with non-uniform cosine rotation angle inflow
图 22 余旋角不均匀进气来流条件下一体化加力燃烧室流场流阻特性
Figure 22. Flow resistance characteristics of integrated afterburner flow field with non-uniform cosine rotation angle inflow
表 1 一体化加力燃烧室进口不均匀度
Table 1. Non-uniform velocity and cosine rotation angle of integrated afterburner inflow
工况 速度
不均匀度$ {\delta }_{\mathrm{v}} $/%余旋角
α/（°）余旋角
不均匀度$ {\delta }_{\alpha } $/%1 0 0 0 2 30 0 0 3 40 0 0 4 50 0 0 5 0 5～15 12.5 6 0 10～20 13.3 7 0 15～25 14.3 
下载: 导出CSV
表 2 均匀来流条件下的进口气流参数
Table 2. Inlet airflow parameters of uniform inflow
参数 数值 参数 数值 总压/kPa 478 总温/K 1350.88 Ma 0.55 质量流量/（kg/s） 21.9593
下载: 导出CSV
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