大涵道比风扇增压级进气畸变性能试验研究

高倩; 杨小贺; 刘世文

doi:10.13224/j.cnki.jasp.20230381

大涵道比风扇增压级进气畸变性能试验研究

doi: 10.13224/j.cnki.jasp.20230381

中国航发商用航空发动机有限责任公司，上海 200241

详细信息

作者简介:
高倩（1989-），女，硕士，主要从事航空发动机风扇/增压级气动研究

通讯作者:
杨小贺（1984-），男，研究员，博士，主要从事航空发动机风扇/增压级气动研究。E-mail：xiaocao710181@163.com

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2023-06-09
- 网络出版日期: 2024-10-29

Experiment on inlet distortion of high bypass ratio fan and booster

Commercial Aircraft Engine Company Limited，Aero Engine Corporation of China，Shanghai 200241，China

摘要

摘要:
针对某大涵道比涡扇发动机，开展了其风扇增压级性能进气总压畸变试验研究，以获取进气畸变对风扇增压级性能的影响。通过试验件进口安装畸变模拟网的形式模拟畸变来流条件。畸变图谱形式来源于短舱进气道风洞吹风试验，总压畸变形式为径向、周向组合畸变。结果表明：进气总压畸变会抬高风扇外涵工作点位置，从而降低外涵喘振裕度；相比均匀进气特性，进气总压畸变条件下风扇外涵换算质量流量和压比有增大趋势，0.3到0.8相对换算转速，换算质量流量增大范围为0.2%到1%；由于畸变区主要集中在外涵区域，风扇增压级内涵特性与均匀进气特性基本相当；畸变进气条件下，风扇进口畸变区静压偏低，经过风扇增压作用后静压快速抬高，支板后静压与均匀进气趋势基本一致。
- 大涵道比 /
- 风扇 /
- 总压畸变 /
- 畸变模拟网 /
- 喘振裕度
Abstract:
Based on a high bypass ratio turbofan engine, experimental investigation on the inlet total pressure distortion of the fan performance was carried out to obtain the fan-booster performance under crosswind conditions and support the engine crosswind test. The inlet total pressure distortion flow under the crosswind conditions was obtained by installing distortion simulation network. The distortion pattern was derived from the wind tunnel test of the engine nacelle. The total pressure distortion pattern included radial distortion and circumferential distortion. The results showed that the total pressure distortion raised the working point of the fan and reduced the surge margin. Compared with the fan performance of uniform flow, the corrected mass flow and total pressure ratio tended to increase, the mass flow ranged from 0.2% to 1%, while the corrected rotational speed ranged from 0.3 to 0.8. The core performance of the inlet total pressure distortion was similar with the performance of uniform flow. The static pressure of inlet total pressure distortion increased rapidly after the fan, and the static pressure behind the struts was basically consistent with that of the uniform flow.
- high bypass ratio /
- fan /
- total pressure distortion /
- distortion simulation network /
- surge margin

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图 1 畸变模拟网示意图

Figure 1. Schematic diagram of distortion network

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图 2 进气畸变发生器示意图

Figure 2. Schematic diagram of distortion generator

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图 3 风扇进口测点布置

Figure 3. Arrangement of measuring points of fan inlet

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图 4 外涵测点布置

Figure 4. Arrangement of measuring points of bypass

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图 5 外涵出口测点布置

Figure 5. Arrangement of measuring points of bypass outlet

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图 6 内涵测点布置

Figure 6. Arrangement of measuring points of core

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图 7 内涵出口测点布置

Figure 7. Arrangement of measuring points of core outlet

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图 8 数据重复性验证

Figure 8. Verification of measuring repeatability

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图 9 风扇进口来流畸变指数

Figure 9. Distortion index of fan inlet

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图 10 试验测得畸变图谱

Figure 10. Distortion map obtained by test

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图 11 外涵流量-压比特性

Figure 11. Mass flow-pressure ratio performance of bypass

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图 12 内涵流量-压比特性

Figure 12. Mass flow-pressure ratio performance of core

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图 13 周向畸变的影响

Figure 13. Effects of circumferential distortion

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图 14 风扇进口总压剖面

Figure 14. Total pressure profile of fan inlet

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图 15 风扇出口总压剖面

Figure 15. Total pressure profile of fan outlet

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图 16 外涵出口总压剖面

Figure 16. Total pressure profile of bypass outlet

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图 17 外涵压比剖面

Figure 17. Pressure ratio profile of bypass

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图 18 畸变进气和均匀进气情况下外涵静压分布（0.8相对换算转速）

Figure 18. Static pressure distribution of bypass in distortion flow and uniform flow （corrected rotational speed of 0.8）

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表 1 测量探针精度要求

Table 1. Measurement accuracy of probes

测量参数	测量设备	参数精度要求
总压	梳状总压探针	±0.3%
总压	叶型总压探针	±0.3%
总温	梳状总温探针	±1 K
总温	叶型总温探针	±1 K
流量	流量计	±1 kg/s
静压	壁面静压测点	±0.3%

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表 2 不同换算流量下的畸变指数

Table 2. Distortion index at different mass flows

相对换算转速	无量纲流量	畸变指数/%
0.3	0.327	0.69
0.5	0.530	1.91
0.6	0.639	2.86
0.68	0.745	4.11
0.75	0.805	5.00
0.8	0.878	6.15
0.89	1	8.60

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表 3 不同转速下畸变进气裕度损失

Table 3. Distortion margin loss at different speeds

相对换算转速	均匀进气喘振裕度	畸变进气喘振裕度	喘振裕度损失/%
0.3	1.0	1.0	0
0.5	1.0	0.978	3.2
0.6	1.0	0.976	3.4

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