IC10合金高压涡轮导向叶片开裂机理分析  

Analysis of Cracking Mechanism of IC10 Alloy High Pressure Turbine Guide Vane

作　　者：刘明坤 李艳明 王威 迟庆新 魏晓 佟文伟 LIU Ming-kun;LI Yan-ming;WANG Wei;CHI Qing-xin;WEI Xiao;TONG Wen-wei(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2025年第1期165-170,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了给高压涡轮导向叶片寿命损伤评价提供技术支撑,对开裂的IC10合金定向凝固高压涡轮导向叶片开展了叶片宏观检查、断口分析、微观组织检查、化学成分分析、组织热模拟试验及超温力学性能测试等相关工作,确定了裂纹的性质和产生机理。结果表明:叶片裂纹性质是以热应力为主的疲劳裂纹,裂纹起源于叶盆侧内腔靠近气膜孔和加强筋的表面。高低温变化的工作环境及叶片自身不均匀的温度分布,使叶片受到周期性热应力作用。此外,通过组织热模拟试验反推裂纹部位实际工作温度达到了1175~1200℃,超过了IC10合金的长期许用温度1100℃,合金中γ'相退化,降低了叶片的高温强度。在超温条件下的拉伸试验结果进一步表明,随温度的升高,IC10合金的拉伸强度明显降低,合金在超温状态下的抗力不足。热应力和微观组织退化的共同作用导致了疲劳裂纹的萌生和扩展。In order to provide technical support for the life damage evaluation of high-pressure turbine guide vanes,macroscopic inspection,fracture analysis,micro-structure inspection,chemical composition analysis,micro-structure thermal simulation test,and overtemperature mechanical property test were carried out on the cracked IC10 alloy directional solidification high-pressure turbine guide vane to determine the nature and failure mechanism of the cracks.The results show that the crack nature of the vane is mainly fatigue crack induced by thermal stress.The fatigue crack originated from the inner cavity surface of the concave side near the film cooling holes and stiffener.The vane was subjected to periodic thermal stress due to the working environment with varying temperatures and the uneven temperature distribution of the vane.In addition,through thermal simulation tests,it was inferred that the actual operating temperature at the crack site reached 1175-1200℃,exceeding the long-term service temperature of 1100℃of IC10 alloy.The degradation ofγ′phase in the alloy reduced the hightemperature performance of the vane.The high-temperature tensile test results further indicate that the tensile strength of IC10 alloy decreased significantly with the increase of temperature and the resistance of the alloy was insufficient in the over-temperature state.The combined effect of thermal stress and micro-structural degradation led to the initiation and propagation of fatigue cracks.

关 键 词：涡轮导向叶片 疲劳裂纹 热应力 γ’相 失效分析 超温 IC10合金 航空发动机 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]