CAJ | 학술논문

针对某F级重型燃气轮机，根据机组的实际运行监测数据，提取得到该机组在冷态启动、热态启动两种工况下各测点温度随时间的变化曲线，分析得到转子各处的换热边界条件，采用有限元方法计算该燃气轮机转子在不同启动工况下的整机瞬态温度场及应力场，并基于该瞬态热应力分析结果对转子的低周疲劳寿命损耗进行评估。计算结果表明：最大热弹性应力值一般都出现在透平第一级轮盘的出气侧底部圆角处及压气机后三级轮盘的中间部位的圆角区域；气流参数变化的快慢对转子应力分布影响极大；冷态启动一次的寿命损耗最高达0.02%，大于热态启动的对应值。研究结果为轮盘结构设计与机组运行规程的优化提供了重要参考。
침대모F급중형연기륜궤，근거궤조적실제운행감측수거，제취득도해궤조재랭태계동、열태계동량충공황하각측점온도수시간적변화곡선，분석득도전자각처적환열변계조건，채용유한원방법계산해연기륜궤전자재불동계동공황하적정궤순태온도장급응력장，병기우해순태열응력분석결과대전자적저주피로수명손모진행평고。계산결과표명：최대열탄성응력치일반도출현재투평제일급륜반적출기측저부원각처급압기궤후삼급륜반적중간부위적원각구역；기류삼수변화적쾌만대전자응력분포영향겁대；랭태계동일차적수명손모최고체0.02%，대우열태계동적대응치。연구결과위륜반결구설계여궤조운행규정적우화제공료중요삼고。
Taking a specific heavy-duty gas turbine of F class as study obj ect,based on the monito-ring data of actual operation,curves denoting temperature changes over time of measuring points in the F class heavy-duty gas turbine unit were extracted at cold starting and hot starting conditions.In these two starting conditions,the heat transfer boundary conditions were calculated throughout,the finite element method was used to analyze the transient temperature field and stress field of the gas turbine rotor in different starting conditions.Based on the results,the low-cycle fatigue life loss was assessed.The calculation results show that maximum thermal elastic stress generally appears at the bottom fillet on the outlet side of the turbine’s first stage disc and rounded area on the middle part of the compressor’s third stage disc;airflow parameter change speed has enormous influences on the ro-tor’s stress distribution and the life loss of cold starting is up to 0.02%,greater than the correspond-ing value of the hot starting.The conclusion provides an important reference for the optimization of wheel structure design and the unit operating procedures.