离心叶轮背腔旋流抑制技术设计及验证

张远森; 周志翔; 郝旭生; 赵尊盛; 陈杜; 吴楠

doi:10.13224/j.cnki.jasp.20230136

离心叶轮背腔旋流抑制技术设计及验证

doi: 10.13224/j.cnki.jasp.20230136

中国航发湖南动力机械研究所，湖南株洲 412002

详细信息

作者简介:
张远森（1988-），男，高级工程师，硕士，主要从事发动机空气系统与传热研究

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2023-03-07
- 网络出版日期: 2024-06-18

Design and validate about swirl velocity restrain on cavity behind centrifugal impeller disk

Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
基于旋转盘腔径向外流科氏力作用理论，开展了叶轮背腔旋流抑制引气方案设计，并通过数值计算对设计方案进行了评估，结果表明：叶轮背腔径向外流引气方案由科氏力起主导作用，可抑制叶轮背腔旋转比，提高引气出口静压系数至0.88，较常规方案A增加16.6%，增大了叶轮背腔向前的轴向力，可起到调节发动机在慢车等低状态的转子轴向力轻载、反向的作用，但由于轮背旋转壁面与气流之间的速度差增大，导致轮盘消耗风阻功率增加，引气出口温度增加30 K，并在旋转换热实验台上对该技术进行了验证。
- 叶轮背腔 /
- 径向外流 /
- 旋转比 /
- 轴向力 /
- 功耗
Abstract:
Base on the theory about Coriolis force on rotate cavity, the project to restrain swirl ratio on the cavity behind centrifugal impeller disk was designed, and then analyzed by the numerical tool. The result showed that: the project about radial outer flow on the cavity behind centrifugal impeller disk was dominated by the Coriolis force, which can restrain the swirl ratio and increase the static pressure coefficient to 0.88 on the cavity exit, the static pressure coefficient increased by 16.6% compared to plan A, so it can increase the axial force on the cavity behind impeller disk and improve the light load of bearing and reverse the direction of axial force at small state. But due to the great velocity diversity between rotation wall and air, the power wasting on the cavity behind impeller disk increased, the temperature of air exit increased to 30 K. The result was validated on rotating heat exchange coefficient testing stand.
- cavity behind impeller disk /
- radial outer flow /
- swirl ratio /
- axial force /
- power wasting

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图 1 旋转盘腔的气流受力

Figure 1. Force of air in rotate cavity

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图 2 科氏力的方向

Figure 2. Direction of Coriolis force

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图 3 旋流抑制引气方案

Figure 3. Case of swirl velocity restrain

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图 4 叶轮背腔网格

Figure 4. Mesh of cavity behind impeller disk

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图 5 叶轮背腔边界划分

Figure 5. Defined boundary of cavity behind impeller disk

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图 6 速度矢量图

Figure 6. Figures of velocity vector

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图 7 旋转比分布

Figure 7. Distribution of swirl ratio

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图 8 静压系数分布

Figure 8. Distribution of static pressure coefficient

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图 9 盘腔总温分布

Figure 9. Total temperature on cavity

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图 10 旋转盘腔实验台

Figure 10. Testing bench of rotate cavity

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图 11 PIV测量系统布置图

Figure 11. Sketch map of PIV measure project

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图 12 旋转比计算和测试数据对比

Figure 12. Comparison of swirl ratio data for calculation and testing

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表 1 数值计算边界

Table 1. Boundary of numerical calculation

参数	数值
参数	方案A	方案B
转速/（r/min）	25248	25248
主流进口总温/K	754	754
主流进口轴向速度/（m/s）	0	0
主流进口径向速度/（m/s）	165	165
主流进口切向速度/（m/s）	445	445
主流出口静压/kPa	1380	1380
盘腔出口背压/kPa	980	1144
盘腔引气质量流量/（g/s）	210	210
流道换热面传热系数/（W/（m²·K））	1 980	1 980
流道换热面温度/K	606	606

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表 2 叶轮背腔的压力

Table 2. Pressure of cavity behind impeller disk

项目	方案A	方案B	增幅/%
调压板底部内径比		0.6r
出口静压系数	0.752	0.877	16.6
平均静压系数	0.891	0.94	5.5

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表 3 转子轴向力计算结果

Table 3. Calculation result of axial force on rotor N

工况	方案A		方案B
工况	叶轮背腔	总和	叶轮背腔	总和
地面慢车	−27342	588	−28479	−549
最大起飞	−137043	−2862	−144550	−10368

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表 4 不同方案的温度和功耗

Table 4. Temperature and power wasting about different projects

项目	方案A	方案B
引气温度/K	754	754
排气温度/K	784	814
轮盘功耗/kW	17.6	27.3
气流吸热/kJ	6.33	12.66
轮盘吸热/kJ	11.31	14.66

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