燃气轮机尾筒密封件增设热障涂层与挂机运行实验

Spray Thermal Barrier Coatings and Hanging Machine Experiment for Gas Turbine Transition Piece Seal

基于第1轮燃气轮机国产化制造的经验与教训,提出了更为稳健的军民融合技术开发思路,对新采购到货的尾筒密封件通流外表面增设热障涂层。选用航空发动机修理用的先进涂层材料并研发了适用于燃气轮机的热障涂层制备工艺技术,完成了样品研制,分别在连续运行以及两班制运行的联合循环机组上进行了挂机实验。结果显示,涂层材料经受住了至少1个检修周期的运行考验,一些产品实现了延寿2个检修周期的目标,一些产品未能实现延寿至少1个检修周期的正常预期目标。部分实验未达到预期延寿目标主要是受限于尾筒密封件基材性能,其次是涂层制备工艺不稳定。提出热障涂层材料与制备工艺的技术改进设想,总结了主要成果、教训和不足之处。

On the basis of summing up experience and drawing lessons of the first round localization manufacturing of transition piece seal for heavy duty gas turbine,a more robust technology development route was proposed,TBC(thermal barrier coating)was added to the outer surface of the flow path of the newly purchased transition piece seals.Advanced TBC material for repairing aero-engine was selected,the preparation technology suitable for gas turbine was developed,the sample was completed,and then hanging machine experiments were carried out with groups and sets of transition piece seal in different power plants by base-load or DSS(daily start-shutdown)operation mode.Results showed TBC material had withstood at least one maintenance interval and could meet the requirements of actual operation,some products achieved the optimal goal of extending the life of two maintenance intervals,while some products failed to achieve the normal expected goal of extending the life of at least one maintenance interval.Analysis showed that the main reasons for some products failed to achieve the normal expected goal of extending the life was likely to be affected by base material performance and instability of the coating preparation technology.This paper proposed some improvement ideas on TBC material and preparation technology,and summarized the main achievements,shortcomings and lessons.