IMR OpenIR
Investigation and simulation of the shear lip phenomenon observed in a high-speed abradable seal for use in aero-engines
Xue, Weihai; Gao, Siyang; Duan, Deli; Zheng, Hailiang; Li, Shu; Duan, DL (reprint author), Chinese Acad Sci, Inst Met Res, Shenyang 110016, Liaoning, Peoples R China.
2017-09-15
发表期刊WEAR
ISSN0043-1648
卷号386-387页码:195-203
摘要Abradable seals are used in the compressor sections of aero-engines, and their performance affects engine efficiency and durability. The sliding-induced surface damage between a type GH4169 turbine blade and a CuAlNiG seal coating was investigated under simulated working conditions using an improved high-speed rubbing test rig. The influence of different linear speeds (150, 300 m/s), incursion rates (5, 50, 500 mu m/s) and environment temperatures (300, 450 degrees C) were researched. According to variations in weight and height measurements of the blade test samples, and based on observations of the blade wear scar macro-morphologies, it was found that blade wear with a prominent shear lip increases with linear speed and temperature but decreases with incursion rate. The surface and cross-section morphologies, phase components of the blade and coating wear scars were analyzed using SEM, EDS and XRD. The formation mechanism of the shear lip was revealed for the first time. It was found that a double-layer shear lip was produced by the combined action of a shear mixed layer and blade matrix softening, both of which resulted from high-intensity frictional heating. (C) 2017 Elsevier B.V. All rights reserved.; Abradable seals are used in the compressor sections of aero-engines, and their performance affects engine efficiency and durability. The sliding-induced surface damage between a type GH4169 turbine blade and a CuAlNiG seal coating was investigated under simulated working conditions using an improved high-speed rubbing test rig. The influence of different linear speeds (150, 300 m/s), incursion rates (5, 50, 500 mu m/s) and environment temperatures (300, 450 degrees C) were researched. According to variations in weight and height measurements of the blade test samples, and based on observations of the blade wear scar macro-morphologies, it was found that blade wear with a prominent shear lip increases with linear speed and temperature but decreases with incursion rate. The surface and cross-section morphologies, phase components of the blade and coating wear scars were analyzed using SEM, EDS and XRD. The formation mechanism of the shear lip was revealed for the first time. It was found that a double-layer shear lip was produced by the combined action of a shear mixed layer and blade matrix softening, both of which resulted from high-intensity frictional heating. (C) 2017 Elsevier B.V. All rights reserved.
部门归属[xue, weihai ; gao, siyang ; duan, deli ; li, shu] chinese acad sci, inst met res, shenyang 110016, liaoning, peoples r china ; [zheng, hailiang] aero engine grp corp china, shenyang inst engine design, shenyang 110015, liaoning, peoples r china
关键词Seal Coating High-speed Rubbing Gh4169 Blade Compressor Blades Blade Shear Lip
学科领域Engineering, Mechanical ; Materials Science, Multidisciplinary
资助者National Natural Science Foundation of China [50675215]; Tribology Science Fund of State Key Laboratory of Tribology and Innovation [SKLTKF15B09]
收录类别SCI
语种英语
文献类型期刊论文
条目标识符http://ir.imr.ac.cn/handle/321006/78011
专题中国科学院金属研究所
通讯作者Duan, DL (reprint author), Chinese Acad Sci, Inst Met Res, Shenyang 110016, Liaoning, Peoples R China.
推荐引用方式
GB/T 7714
Xue, Weihai,Gao, Siyang,Duan, Deli,et al. Investigation and simulation of the shear lip phenomenon observed in a high-speed abradable seal for use in aero-engines[J]. WEAR,2017,386-387:195-203.
APA Xue, Weihai,Gao, Siyang,Duan, Deli,Zheng, Hailiang,Li, Shu,&Duan, DL .(2017).Investigation and simulation of the shear lip phenomenon observed in a high-speed abradable seal for use in aero-engines.WEAR,386-387,195-203.
MLA Xue, Weihai,et al."Investigation and simulation of the shear lip phenomenon observed in a high-speed abradable seal for use in aero-engines".WEAR 386-387(2017):195-203.
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