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Article(id=1244336753050497923, tenantId=1146029695717560320, journalId=1244311425741537314, issueId=1244336743298740932, articleNumber=null, orderNo=null, doi=10.16450/j.cnki.issn.1004-6801.2025.05.011, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1684944000000, receivedDateStr=2023-05-25, revisedDate=1688918400000, revisedDateStr=2023-07-10, acceptedDate=null, acceptedDateStr=null, onlineDate=1774602600585, onlineDateStr=2026-03-27, pubDate=1759248000000, pubDateStr=2025-10-01, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1774602600585, onlineIssueDateStr=2026-03-27, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1774602600585, creator=13701087609, updateTime=1774602600585, updator=13701087609, issue=Issue{id=1244336743298740932, tenantId=1146029695717560320, journalId=1244311425741537314, year='2025', volume='45', issue='5', pageStart='855', pageEnd='1056', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=-1, specialIssue=null, createTime=1774602598261, creator=13701087609, updateTime=1774603435030, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1244340253042000577, tenantId=1146029695717560320, journalId=1244311425741537314, issueId=1244336743298740932, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1244340253042000578, tenantId=1146029695717560320, journalId=1244311425741537314, issueId=1244336743298740932, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=937, endPage=943, ext={EN=ArticleExt(id=1244336753402819475, articleId=1244336753050497923, tenantId=1146029695717560320, journalId=1244311425741537314, language=EN, title=Research on Characteristics of Typical Gas Path Fault Components in Aircraft Engines, columnId=1244336744728998604, journalTitle=Journal of Vibration,Measurement and Diagnosis, columnName=PAPER, runingTitle=null, highlight=null, articleAbstract=

In response to unclear mechanisms in compressor fault diagnosis research，this article aims to reveal the variation law of component characteristic changes caused by blade wear，numerical simulation analysis method is used for studying the changes in component characteristics of blades under different degrees of wear. The results show that the degree of compressor performance degradation caused by blade surface wear is more significant than that caused by blade tip wear. With the increased speed，the degree of performance degradation becomes greater. The efficiency decay value caused by the increase of blade tip clearance shows a pattern of first decreasing and then increasing with the increase of pressure ratio. Near the working line of the compressor，the efficiency decay value is relatively stable with the change of pressure ratio，while the flow decay value increases with the increase of pressure ratio. After the increase of blade surface roughness，the decay values of efficiency and flow rate both increase with the increase of pressure ratio. Moreover，there is a decreasing trend in the decay values near stall pressure ratio. Near the working line，varying degrees of blade wear have a greater impact on flow rate than on efficiency. The results can provide a theoretical reference for the research of fault diagnosis methods for aviation engine gas paths.

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针对压气机故障诊断中机理不清晰的问题，为了揭示叶片磨损后压气机部件特性偏差的变化规律，通过数值仿真分析方法研究了叶片在不同磨损程度下的部件特性变化规律。结果表明：叶片表面磨损相比于叶尖磨损引起的压气机性能衰退程度更明显，且转速越高，性能衰退的程度越大；叶尖间隙增大导致的效率衰退值随着压比增大呈现出先减小后增大的规律，其中在压气机的工作线附近，效率的衰退值随压比变化较为稳定，而流量衰退值随压比的增大而增大；叶片表面粗糙度增大后效率和流量的衰退值都随压比的增大而增大，在接近失速的压比下衰退值有减小的趋势；在工作线附近，不同程度的叶片磨损对流量的影响大于对效率的影响。该结果可为航空发动机气路故障诊断方法的研究提供理论参考。

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耿佳，男，1987年8月生，博士、副研究员。主要研究方向为发动机气路故障诊断。 E-mail：
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王净巍，女，1991年4月生，硕士、工程师。主要研究方向为发动机故障诊断。 E-mail:

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王净巍，女，1991年4月生，硕士、工程师。主要研究方向为发动机故障诊断。 E-mail:

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王净巍，女，1991年4月生，硕士、工程师。主要研究方向为发动机故障诊断。 E-mail:

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ArticleFig(id=1244351820617859166, tenantId=1146029695717560320, journalId=1244311425741537314, articleId=1244336753050497923, language=CN, label=图14, caption=不同叶片磨损模式下沿叶高方向静熵分布, figureFileSmall=b0RITmeECim7yGzj92/qtA==, figureFileBig=of4RBtobVbyAm7M+SA5ZiA==, tableContent=null), ArticleFig(id=1244351820726911078, tenantId=1146029695717560320, journalId=1244311425741537314, articleId=1244336753050497923, language=EN, label=Tab.1, caption=

Calculation scheme settings

, figureFileSmall=null, figureFileBig=null, tableContent=
方案转速间隙ks/μmRa/μm
11.0N/0.8N/0.6N1.00T00
21.0N/0.8N/0.6N1.25T00
31.0N/0.8N/0.6N1.50T00
41.0N/0.8N/0.6N1.75T00
51.0N/0.8N/0.6N2.00T00
61.0N/0.8N/0.6N2.50T00
71.0N/0.8N/0.6N1.00T50.8
81.0N/0.8N/0.6N1.00T101.6
91.0N/0.8N/0.6N1.00T304.8
101.0N/0.8N/0.6N1.00T508.0
111.0N/0.8N/0.6N1.00T7011.2
121.0N/0.8N/0.6N1.50T304.8
), ArticleFig(id=1244351820814991471, tenantId=1146029695717560320, journalId=1244311425741537314, articleId=1244336753050497923, language=CN, label=表1, caption=

计算方案设置

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方案转速间隙ks/μmRa/μm
11.0N/0.8N/0.6N1.00T00
21.0N/0.8N/0.6N1.25T00
31.0N/0.8N/0.6N1.50T00
41.0N/0.8N/0.6N1.75T00
51.0N/0.8N/0.6N2.00T00
61.0N/0.8N/0.6N2.50T00
71.0N/0.8N/0.6N1.00T50.8
81.0N/0.8N/0.6N1.00T101.6
91.0N/0.8N/0.6N1.00T304.8
101.0N/0.8N/0.6N1.00T508.0
111.0N/0.8N/0.6N1.00T7011.2
121.0N/0.8N/0.6N1.50T304.8
), ArticleFig(id=1244351820928237684, tenantId=1146029695717560320, journalId=1244311425741537314, articleId=1244336753050497923, language=EN, label=Tab.2, caption=

The influence of compressor on component characteristics under different fault conditions

, figureFileSmall=null, figureFileBig=null, tableContent=
故障情况衰退量内容当前转速/设计点转速
60%80%100%
1.25T效率0.307~0.3510.348~0.3530.314~0.437
流量0.883~1.1000.662~1.0330.192~1.623
1.50T效率0.599~0.6570.656~0.6750.604~0.695
流量1.662~2.0341.285~1.8570.406~1.884
1.75T效率0.878~0.9560.942~0.9880.870~0.931
流量2.193~2.9971.662~2.6940.756~2.290
2.00T效率1.158~1.2561.228~1.3051.143~1.171
流量2.591~3.6261.909~3.4171.097~2.503
2.50T效率1.651~1.7601.754~1.8141.686~1.742
流量3.654~4.7232.418~4.1911.500~3.187
5 μm效率0.329~0.3550.371~0.3990.292~0.443
流量0.576~0.9510.496~0.9410.625~1.144
10 μm效率0.598~0.6370.633~0.6930.539~0.760
流量0.837~1.4830.698~1.4341.078~1.739
30 μm效率1.260~1.6261.299~1.4131.066~1.509
流量1.773~2.9791.543~3.0552.388~3.735
50 μm效率1.674~1.7221.739~1.8081.202~1.890
流量3.247~4.6593.401~4.8003.208~5.344
70 μm效率1.941~2.0171.946~2.1201.304~2.136
流量4.671~6.4164.971~6.0923.827~6.359
1.5T及30 μm效率1.815~2.0051.815~2.0051.815~2.005
流量3.374~4.4323.374~4.4323.374~4.432
), ArticleFig(id=1244351821066649723, tenantId=1146029695717560320, journalId=1244311425741537314, articleId=1244336753050497923, language=CN, label=表2, caption=

压气机在不同故障情况下对部件特性的影响

, figureFileSmall=null, figureFileBig=null, tableContent=
故障情况衰退量内容当前转速/设计点转速
60%80%100%
1.25T效率0.307~0.3510.348~0.3530.314~0.437
流量0.883~1.1000.662~1.0330.192~1.623
1.50T效率0.599~0.6570.656~0.6750.604~0.695
流量1.662~2.0341.285~1.8570.406~1.884
1.75T效率0.878~0.9560.942~0.9880.870~0.931
流量2.193~2.9971.662~2.6940.756~2.290
2.00T效率1.158~1.2561.228~1.3051.143~1.171
流量2.591~3.6261.909~3.4171.097~2.503
2.50T效率1.651~1.7601.754~1.8141.686~1.742
流量3.654~4.7232.418~4.1911.500~3.187
5 μm效率0.329~0.3550.371~0.3990.292~0.443
流量0.576~0.9510.496~0.9410.625~1.144
10 μm效率0.598~0.6370.633~0.6930.539~0.760
流量0.837~1.4830.698~1.4341.078~1.739
30 μm效率1.260~1.6261.299~1.4131.066~1.509
流量1.773~2.9791.543~3.0552.388~3.735
50 μm效率1.674~1.7221.739~1.8081.202~1.890
流量3.247~4.6593.401~4.8003.208~5.344
70 μm效率1.941~2.0171.946~2.1201.304~2.136
流量4.671~6.4164.971~6.0923.827~6.359
1.5T及30 μm效率1.815~2.0051.815~2.0051.815~2.005
流量3.374~4.4323.374~4.4323.374~4.432
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航空发动机气路故障部件特性变化规律
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王净巍 1 , 余壮 2, 3 , 姚远 2, 3 , 耿佳 2, 3
振动、测试与诊断 | 论文 2025,45(5): 937-943
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振动、测试与诊断 | 论文 2025, 45(5): 937-943
航空发动机气路故障部件特性变化规律
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王净巍1 , 余壮2, 3, 姚远2, 3, 耿佳2, 3
作者信息
  • 1中国航发沈阳发动机研究所　沈阳，110015
  • 2西安交通大学机械工程学院　西安，710049
  • 3航空动力系统与等离子体技术全国重点实验室　西安，710049

    • 王净巍，女，1991年4月生，硕士、工程师。主要研究方向为发动机故障诊断。 E-mail:

通讯作者:

耿佳，男，1987年8月生，博士、副研究员。主要研究方向为发动机气路故障诊断。 E-mail：
Research on Characteristics of Typical Gas Path Fault Components in Aircraft Engines
Jingwei WANG1 , Zhuang YU2, 3, Yuan YAO2, 3, Jia GENG2, 3
Affiliations
  • 1.Shenyang Engine Research Institute of AVIC　Shenyang，110015，China
  • 2.School of Mechanical Engineering，Xi'an Jiaotong University　Xi'an，710049，China
  • 3.National Key Lab of Aerospace Power System and Plasma Technology　Xi'an，710049，China
出版时间: 2025-10-01 doi: 10.16450/j.cnki.issn.1004-6801.2025.05.011
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摘要
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针对压气机故障诊断中机理不清晰的问题，为了揭示叶片磨损后压气机部件特性偏差的变化规律，通过数值仿真分析方法研究了叶片在不同磨损程度下的部件特性变化规律。结果表明：叶片表面磨损相比于叶尖磨损引起的压气机性能衰退程度更明显，且转速越高，性能衰退的程度越大；叶尖间隙增大导致的效率衰退值随着压比增大呈现出先减小后增大的规律，其中在压气机的工作线附近，效率的衰退值随压比变化较为稳定，而流量衰退值随压比的增大而增大；叶片表面粗糙度增大后效率和流量的衰退值都随压比的增大而增大，在接近失速的压比下衰退值有减小的趋势；在工作线附近，不同程度的叶片磨损对流量的影响大于对效率的影响。该结果可为航空发动机气路故障诊断方法的研究提供理论参考。

气路磨损故障  /  叶尖间隙  /  叶片表面粗糙度  /  性能衰退

In response to unclear mechanisms in compressor fault diagnosis research，this article aims to reveal the variation law of component characteristic changes caused by blade wear，numerical simulation analysis method is used for studying the changes in component characteristics of blades under different degrees of wear. The results show that the degree of compressor performance degradation caused by blade surface wear is more significant than that caused by blade tip wear. With the increased speed，the degree of performance degradation becomes greater. The efficiency decay value caused by the increase of blade tip clearance shows a pattern of first decreasing and then increasing with the increase of pressure ratio. Near the working line of the compressor，the efficiency decay value is relatively stable with the change of pressure ratio，while the flow decay value increases with the increase of pressure ratio. After the increase of blade surface roughness，the decay values of efficiency and flow rate both increase with the increase of pressure ratio. Moreover，there is a decreasing trend in the decay values near stall pressure ratio. Near the working line，varying degrees of blade wear have a greater impact on flow rate than on efficiency. The results can provide a theoretical reference for the research of fault diagnosis methods for aviation engine gas paths.

air circuit wear failure  /  tip clearance  /  blade surface roughness  /  performance degradation
王净巍, 余壮, 姚远, 耿佳. 航空发动机气路故障部件特性变化规律. 振动、测试与诊断, 2025 , 45 (5) : 937 -943 . DOI: 10.16450/j.cnki.issn.1004-6801.2025.05.011
Jingwei WANG, Zhuang YU, Yuan YAO, Jia GENG. Research on Characteristics of Typical Gas Path Fault Components in Aircraft Engines[J]. Journal of Vibration,Measurement and Diagnosis, 2025 , 45 (5) : 937 -943 . DOI: 10.16450/j.cnki.issn.1004-6801.2025.05.011
正文
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引言
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在航空发动机健康管理系统中，气路故障诊断技术占据了重要的地位［1］。发动机状态预测及健康管理的研究工作是建立在大量数据基础上开展的，而实际中机组能够获取的故障数据量具有很大的局限性，难以通过收集到的真实数据构建有效的气路故障诊断系统。目前，应用最广泛的方法是以发动机的性能模型为基础，通过给定气路部件的效率和流量偏差系数［2］，进行发动机典型气路故障的模拟分析［3］，从而获取大量的仿真故障数据，用于发动机气路故障诊断方法的研究和验证工作［4］。
航空发动机长期在恶劣环境下运行，而压气机处于机体前端，更容易受到空气中的风沙、冰晶、盐雾、化学污染物及机械磨损的影响，导致叶片磨损、叶尖间隙增大以及叶片表面粗糙度增加，从而降低压气机的性能，这是外场维护中最常见的气路故障模式之一。为了提升压气机气路故障诊断方法的可靠性，在对其进行有效性验证的过程中，需要丰富且完整的故障数据。在结合发动机性能模型和气路部件效率、流量偏差系数等参数，对不同压气机气路故障进行模拟的过程中，需要有效的部件特性变化机理作为理论依据。针对此问题，国内外开展了大量的研究工作。孙海鸥等［5］针对某型1.5级轴流压气机进行了数值模拟研究，在额定流量条件下，发现间隙值增加1%弦长时，效率和压比分别下降0.6%和0.17%。Graf等［6］通过实验发现，非均匀叶尖间隙使峰值效率降低了0.4%，最大压比降低了8%，周向非均匀叶尖间隙与最大均匀叶尖间隙对转子的失速点影响接近。Aldi等［7］对NASA Stage37压气机进行数值仿真，研究了污染导致的压气机粗糙度增加对总体性能衰退和内部流场特征的影响，得出了粗糙度对于跨音速压气机性能影响的规律。李飞［8］对具有均匀粗糙度和非均匀粗糙度的压气机叶片进行仿真，讨论了叶片表面粗糙度位置的不同对压气机性能损失的影响，并分析了动静叶吸力面和压力面不同叶片粗糙度的改变与压气机性能损失之间的关系。
尽管现有研究探讨了叶片磨损后峰值流量下的效率和压比衰退值，但为了使基于性能模型的气路故障数据模拟更接近实际情况，实现高逼真度的故障数据模拟，有必要对叶片磨损的压气机在不同工况、不同压比下流量和效率特性偏差比率的变化规律进行研究。为此，笔者结合数值计算方法对轴流式压气机存在表面磨损时的运行状态进行了模拟分析，讨论了压气机表面存在磨损时对应的部件特性变化机理，为发动机气路故障诊断方法和故障数据生成方法提供理论依据。
1　数值计算方法
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1.1　计算方法与条件
以实验室某单级压气机为研究对象，采用TurboGrid软件进行网格划分，对压气机转子采用单通道网格，网格拓扑结构采用O4H型，进出口通道使用H型网格，叶片使用O型网格，并增加了近壁处的网格数量。单通道三维网格与叶片前缘网格细节如图1所示。
数值计算使用CFX求解器，设为定常流动，采用适应逆压力梯度较好的湍流模型，选取方案为高精度的迎风格式和湍流数值方法。压气机的进口设置为总温和总压边界，总温为288.15 K，总压为101 325 Pa；出口设置为平均静压边界条件，并通过修改出口静压值来计算压气机的特性曲线及性能参数。叶片、轮毂和机匣等壁面设置为绝热无滑移的边界条件，叶片通道两侧设置为周期性边界条件。当仿真中转子气边区域流场出现大面积回流导致质量流量急剧下降时，认为压气机进入了失速状态。
为了表现叶片磨损对压气机的影响，本研究将其对叶片形态产生的变化分为叶尖间隙增大和叶片表面粗糙度增大。对于叶尖间隙增大的模拟，以设计的叶尖间隙（T=0.506 mm）为基准，通过不断减小叶片高度来增大叶尖间隙值，直到2.5倍设计叶尖间隙。对于叶片粗糙度的模拟，以计算流体力学前处理模块中粗糙壁面的设定方法给定等效砂粒粗糙度ks，使用Scalable壁面函数，参考国内外针对真实服役的航空发动机的叶片表面轮廓平均偏差Ra的范围研究［9］，并根据Ra与ks的经验关系ks=6.2Ra，对等效砂粒粗糙度进行换算［10‑12］。对于不同的运行工况，分别设置了100%、80%和60%的设计转速（设计转速为N）。计算方案设置见表1，其中出口条件均为给定静压。
1.2　网格无关性验证
为了验证网格数量对计算结果的影响，本研究设置了4种不同数量的网格，分别命名为Grid1、Grid2、Grid3和Grid4，其具体网格数量分别为493 578、1 010 808、1 557 360和1 979 680。对4种网格进行计算，得到压气机的特性曲线，以进行网格无关性验证。不同网格数特性曲线对比如图2所示。其中，横坐标为以压气机设计流量为基准进行无量纲化得到的无量纲流量。可以看出：4套网格计算得到的特性曲线整体趋势相同，随着网格的密度增大，效率有所增加，而总压比有所下降；在每个工况下，通过Grid3和Grid4获得的特性曲线几乎完全重合，而使用网格数量较低的Grid1和Grid2计算得到结果相差较大。可见，Grid3已经达到了网格无关性要求。因此，综合计算精度和计算所耗的资源，本研究选择Grid3网格进行后续计算。
2　计算结果与分析
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2.1　总体性能分析
设计转速下不同叶片磨损情况效率、压比与流量特性对比分别如图3、4所示。其中：点划线代表无故障压气机；实线代表只发生叶尖间隙增大的压气机；双划线代表只发生叶片粗糙度增大的压气机；点线代表叶尖间隙和叶片粗糙度同时增大的压气机。
由图可以发现，相比于无故障叶片，不同程度的叶尖磨损和叶片表面磨损均会导致压气机性能衰退。叶尖间隙增大，效率和压比特性曲线均向下偏移，堵塞流量变化较小。叶片表面粗糙度增大，效率和压比特性曲线更偏向左下方移动，其中：曲线向左偏移是因为气流通过叶片时会遭遇更多的摩擦力，导致流量减小，进而对气体的做功量减小；曲线向下偏移则是因为压气机内部损失增加，由摩擦导致的能量耗散量增加，压气机轴功向压缩气体的有效功转化量减小，且叶片粗糙度增大相比于叶尖间隙增大引起的压气机性能衰退程度更大一些。
通过计算发现在一定的叶尖磨损程度内，效率下降的程度与叶尖间隙值的大小呈近似线性关系。对于本研究中的压气机，其叶尖间隙每增大0.5%叶高，近失速工况点、峰值效率工况点和近堵塞工况点的效率分别会下降0.23%、0.33%和0.4%左右。叶片表面磨损导致的性能衰退比例与等效砂粒粗糙度没有线性关系，随着粗糙程度的增加，压气机的性能对这种故障形式的敏感度逐渐降低，等效砂粒粗糙度ks从5 μm增加到10 μm，峰值效率衰退值增加了0.33%；而ks从10 μm增加到70 μm，每增大20 μm，峰值效率衰退值分别只增加了0.81%、0.51%和0.38%。由于粗糙度增加导致的堵塞作用，在峰值效率流量和堵塞流量之间，叶片磨损导致的压比下降程度明显大于叶尖间隙的增大。而叶尖间隙增大更容易导致流动失稳，在近失速流量下压比下降程度更大。
当叶尖间隙为1.5T、ks为0 μm时，峰值效率下降0.67%，对应流量下压比下降0.26%；当叶尖间隙为1T、ks为30 μm时，峰值效率下降1.01%，对应流量下压比下降0.31%；当叶尖间隙为1.5T、ks为30 μm时，峰值效率下降2.25%，对应流量下压比下降0.70%。两种故障形式同时作用时，压气机性能衰退值大于其单独发生时叠加后的衰退值。
不同转速下压气机特性曲线如图5所示。由图可知：在100%、80%和60%设计转速下，压气机峰值效率变化不大，压比在低转速时下降较多；随着转速的增大，压气机稳定运行的范围逐渐变小；随着转速的降低，气路故障导致压气机在同一流量下效率和压比的衰退程度逐渐减弱。
2.2　叶片磨损对压气机部件特性的影响
使用发动机部件级模型进行仿真时，模型内置的部件特性关系通常采用总压比作为自变量，在模型进行迭代计算时，通过当前的转速和压比找到对应的效率和流量参数［13‑14］。因此，为了更有效地表征叶尖磨损故障对压气机性能衰退的影响，笔者使用相同压比下的流量特性和效率特性的偏差来表征气路故障的影响。
不同叶尖间隙值效率偏差变化和流量偏差变化分别如图6、7所示。由图6可知，在设计转速下，效率的偏差比率在压气机几乎处于堵塞状态时最小，从近堵塞工况到近失速工况过程中，因为叶尖间隙增大导致的效率衰退值呈现出先减小后增大的规律，而在压气机的工作线附近（压比为1.58左右），效率的衰退值较为稳定。随着叶尖间隙值的增大，效率衰退值稳定的范围也不断缩小。叶尖间隙增大到无故障时的2.5倍时，压气机工作压比下的效率偏差比率为-1.69%，在接近失速时可达-2.6%。
与效率特性不同，流量特性的变化与压比正相关，压比越大，流量下降的越快，叶尖间隙增大后与无故障时的流量衰退比例也增加的越快。由图7可知，在设计转速下，在近堵塞的范围内，叶尖间隙值增大造成的流量衰退可忽略不计，而接近失速时造成的流量衰退可达10%。在压气机工作压比下，叶尖间隙增大到无故障时的1.25倍时，流量下降0.51%；增大到无故障时的2.5倍时，流量下降2.13%。在低转速工况下，部件特性变得更加平缓，并且由于压比范围缩小，只体现出工作压比附近的特性偏差。其变化趋势总体与设计转速下相似，即在工作压比附近，效率衰退比率变化不大，流量衰退比率随压比的增大而增大。低转速下效率和流量的整体偏差比率更小。
不同叶片粗糙度下效率偏差变化和流量偏差变化分别如图8、9所示。在设计转速下，从堵塞工况到失速工况，叶片粗糙度增大后效率和流量与无故障时的偏差比率都呈现先增大后减小的趋势，这与叶尖间隙增大导致的特性变化趋势不同。由于叶片表面粗糙度增大导致附面层变厚所引起的堵塞作用以及近失速时的不稳定性，所以在工作压比至近失速工况时的衰退程度较大。在更接近失速压比时，由于摩擦力增大引起压气机流量减小，故特性曲线左移。当粗糙度较低时，压气机性能下降程度较低，导致在某个压比下（1.595~1.600）的特性偏差降低。在近堵塞区域，由于压气机流量相对较大，粗糙度导致相同压比下性能的衰退相对较低。
航空发动机压气机的气路故障诊断中主要参考工作线附近的性能衰退量，因此本研究计算了不同转速、不同叶尖间隙和不同叶片粗糙度下的压气机效率、流量特性在工作压比附近的偏差值。压气机在不同故障情况下对部件特性的影响见表2。
2.3　叶片磨损流场分析
为进一步研究叶片磨损对压气机的影响，选择在设计转速、峰值效率流量下不同叶顶通道的流场进行对比。不同叶尖间隙值99%叶高处峰值效率点相对马赫数（当地气流速度与声速的比值，无量纲参数）分布如图10所示。其中，黑色虚线箭头起于叶片前缘，在吸力面后的红色区域为叶尖泄漏流，这是由于压力面和吸力面的压差作用，使部分气体翻过叶顶通道形成的叶顶泄漏流［15］。由图可以看到，泄漏流在靠近叶片吸力面的通道处与激波相交，并穿过激波与来流交汇后在下一叶片压力面附近形成滞止区，相对马赫数较低，造成较大的损失。当叶尖间隙较大时，泄漏气流的速度和质量流量也随之增加，这会导致气流的旋转和能量损失，对压气机的性能产生负面影响。当叶尖间隙为2T时，正常叶片靠近前缘的激波受到大流量的泄漏流影响而削弱，泄漏流与靠压力面来流相遇形成高损失区域面积也增大，这是导致其效率和压比大幅下降的重要原因。
不同叶尖间隙值99%叶高处峰值效率点静压分布如图11所示，其与相对马赫数云图反映的现象一致。由图可以看出，蓝色的泄漏流穿过激波后在叶片通道内形成面积较大的低压三角区，随着间隙值的增大，低压区影响的范围也逐渐增大到叶片的出口处。
不同粗糙度下90%叶高峰值效率点相对马赫数分布如图12所示。由图可知，叶片表面粗糙度增加后，气体流动的马赫数分布形态变化不显著，但整体马赫数有下降的趋势。叶片表面粗糙度对流动特性的影响主要表现在吸力面激波位置有向叶片前缘移动的趋势上，其幅度增加但作用范围却在缩小，这表明随着粗糙度的增加，压气机流动更容易发生失速的情况。表面更粗糙的叶片降低了气体的流速，从而增加了附面层的厚度，使得气流在通过叶片时的堵塞效应更强，使激波与附面层的相互作用在吸力面更靠近前缘的位置出现，扩大了分离区和尾迹区的范围。此外，粗糙度降低了叶片做功能力，并导致更大的低速区，使得尾迹中的掺混更加剧烈，从而损失也相应增加。这些因素共同导致了压气机的性能衰退。
不同叶片磨损模式下S2流面（指子午流面，即与叶轮旋转轴垂直的平面内的流动截面）静熵云图如图13所示。其展示了设计转速下的峰值效率点在无故障、叶尖间隙增大、表面粗糙度增大以及叶尖间隙和表面粗糙度同时增大的情况下，子午流面的熵增分布。由图可知，各故障形式的静熵分布情况大致相同，主要都在靠近轮毂和机匣处形成了高熵增区域。
结合图10中叶顶间隙的流场结构可以发现，形成高熵增区域的主要原因是由于叶顶间隙泄漏流以及激波与之相互作用形成的二次流。随着叶尖间隙的增大，叶顶的熵增程度和影响的范围也会增加。随着叶片表面粗糙度的增大，整个叶片沿叶高的静熵都较均匀地增加，但是粗糙度的增加也会增大叶顶泄漏流的影响，使得靠近叶顶间隙处的熵增幅度大于靠近轮毂位置的熵增幅度。当间隙值和表面粗糙度同时增大时，叶片出口气流产生了更大的扰动，尤其是在叶片尾缘的熵增最为明显。
不同叶片磨损模式下沿叶高方向静熵分布如图14所示。由图可知，随着叶片磨损程度的提高，轮毂、机匣和叶片出口区域的熵逐渐增大，叶顶、叶根和叶片尾缘出现了严重的流动分离现象。
3　结论
收起
1） 叶片表面磨损相比于叶尖磨损引起的压气机性能衰退程度更大一些，其转速越高，性能衰退的程度越大。两种故障形式同时作用时压气机性能衰退值大于故障单独发生时相加后的衰退值。
2） 叶尖间隙增大时效率衰退值随着压比增大呈现先减小后增大的规律，在压气机的工作线附近，效率的衰退值较为稳定，流量衰退值随着压比的增大而增大。叶片表面粗糙度增大后效率和流量的衰退值都随压比的增大而增大，在接近失速的压比下衰退值有减小的趋势。
3） 叶尖间隙增大导致的泄漏流与通道激波相互作用，泄漏流在穿过激波后在叶片吸力面形成高损失区域，叶尖泄漏流对叶片通道主流的影响集中在80%叶高以上的区域。粗糙叶片降低了气体的流速，增加了附面层的厚度，使得气流在通过叶片时的堵塞效应更强，导致更大的低速区，使得叶片尾缘中的掺混更加剧烈，这些是叶片磨损导致压气机性能衰退的重要因素。
基金
收起
  • 国家重点研发计划资助项目(2022YFF0610903)
  • 国家科技重大专项资助项目(J2019‑I‑0001‑0001)
  • 国家自然科学基金资助项目(52105119)
  • 中国博士后基金资助项目(2020M673378; 2021T140539)
文献
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2025年第45卷第5期
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doi: 10.16450/j.cnki.issn.1004-6801.2025.05.011
  • 接收时间：2023-05-25
  • 首发时间：2026-03-27
  • 出版时间：2025-10-01
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  • 收稿日期：2023-05-25
  • 修回日期：2023-07-10
基金
国家重点研发计划资助项目(2022YFF0610903)
国家科技重大专项资助项目(J2019‑I‑0001‑0001)
国家自然科学基金资助项目(52105119)
中国博士后基金资助项目(2020M673378; 2021T140539)
作者信息
    1中国航发沈阳发动机研究所　沈阳，110015
    2西安交通大学机械工程学院　西安，710049
    3航空动力系统与等离子体技术全国重点实验室　西安，710049

通讯作者:

耿佳，男，1987年8月生，博士、副研究员。主要研究方向为发动机气路故障诊断。 E-mail：
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https://castjournals.cast.org.cn/joweb/zdcsyzd/CN/10.16450/j.cnki.issn.1004-6801.2025.05.011
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2种不同金属材料的力学参数
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Family		 属数
Number of
genus		 种数
Number of
species		 占总种数比例
Percentage of
total species (%)		 属
Genus		 种数
Number of
species		 占总种数比例
Percentage of total
species (%)
鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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