某Ⅰ级涡轮盘低循环疲劳寿命试验研究  

AN EXPERIMENTAL STUDY ON LOW CYCLE FATIGUE LIFE OF 1ST TURBINE DISK IN AEROENGINE

作　　者：龚梦贤[1] 黄庆东[1] 肖育祥[1] 古远兴[1] 赵行明[1] 曹凤兰[1] 

机构地区：[1]燃气涡轮研究院

出　　处：《航空动力学报》1999年第4期361-365,共5页Journal of Aerospace Power

摘　　要：为了确定某Ⅰ级涡轮盘的技术寿命，根据该盘的标准循环载荷谱，对该盘进行了应力分析，确定在标准循环时该盘中心孔与径向销孔相交处为考核部位。为模拟标准循环时该盘在其考核部位的应力谱，专门设计了该Ⅰ级涡轮盘的试验转子及试验参数，在轮盘低循环疲劳试验器上，对该Ⅰ级涡轮盘的一个旧盘进行了高温低循环疲劳试验。试验结果表明：该旧盘低循环疲劳试验至第６０４７ 次循环时，有５ 个销孔考核部位出现了裂纹。断口分析表明：该旧盘剩余的试验低循环疲劳失效寿命为６０４７According to the standard load cycle spectrum,a stress analysis of 1st turbine disk in an aeroengine was completed to determine its useful life.The places,where the centre hole came across the pin holes,were the dangerous points (so called check points).An experimental rotor of the 1st turbine disk had been designed to model the stress spectrum on the check points.The high temperature LCF(low cycle fatigue)test of an old disk was also conducted at SB804-the disk LCF tester in GTE(Gas Turbine Establishment).The test indicated that cracks emerged on the check points of 5 from all of 16 pin holes on the old disk as the 6047th cycle was completed and the crack extended life is 2886 cycles.The comparative analysis of the test results of the old and new disks indicates that LCF crack growth life and fault life with reliability 99 87% and degree of confidence 95% for the 1st turbine disk are 1132 cycles and 2072 cycles respectively.

关 键 词：涡轮盘 低循环疲劳 疲劳寿命 试验 航空发动机 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]