大型燃机热通道整体分析技术研究

Study of general analysis technology of heat passage in large gas turbine

通过对大型 E级燃气轮机的内部性能计算、应力、裂纹计算 ,掌握了机组的性能、流动数值模拟计算、温度和应力计算结果 ,为全面掌握燃机内部性能提供了依据。根据裂纹情况统计分析 ,提出了以叶片损坏区间百分比为特征值的统计方法。统计和计算表明 ,燃机叶片启动、运行一段时间后出现裂纹属于正常情况 ,但通过适当减少启动次数和机组在高温下的运行时间可以推迟裂纹出现的时间和减少裂纹数量。对项目研究结果进行了讨论和应用展望分析 ,主要包括统计结果。

The property of the unit,the flow numerical simulation calculation,the calculating result of temperature and stress were learned through the calculation of internal property,stress and crack of large F class gas turbine to provide evidence for full mastering of internal property of gas tubine.Based on the statistical analysis of cracks,the statistical method which takes the percentage of damaged area in the blade as the eigenvalue was put forward.Statistics and calculation showed that after some operating period of the blade,it is normal to have some cracks,however,the emerging time of the cracks can be deferred and the number of cracks can be reduced by appropriately reducing the start up times and operating time at high temperature.Discussion on the research result and application prospect analysis were carried out,including statistic and calculation result and its application and discussion on the condition assessment of the unit.