航空发动机
航空髮動機
항공발동궤
AERO ENGINE
2011年
6期
36-39
,共4页
场强法%缺口构件%疲劳寿命%燃烧室机匣%安装座
場彊法%缺口構件%疲勞壽命%燃燒室機匣%安裝座
장강법%결구구건%피로수명%연소실궤갑%안장좌
field intensity approach%notch component%fatigue life%combustor casing%installation seat
由于局部应力应变法存在缺陷而引入场强法,对缺口构件的疲劳寿命预测问题进行研究。给出了应力场强法估算缺口构件疲劳寿命的基本框架和分析计算步骤,通过算例对场强法重要参数场径的影响因素、应力集中系数和权函数进行了探讨,并对场强计算中的有限元网格细化问题进行了初步探讨。采用场强法和局部应力应变法对某型发动机燃烧室机匣后衬套安装座进行了疲劳寿命预测。结果表明:利用场强法预测出的寿命更接近试验结果。
由于跼部應力應變法存在缺陷而引入場彊法,對缺口構件的疲勞壽命預測問題進行研究。給齣瞭應力場彊法估算缺口構件疲勞壽命的基本框架和分析計算步驟,通過算例對場彊法重要參數場徑的影響因素、應力集中繫數和權函數進行瞭探討,併對場彊計算中的有限元網格細化問題進行瞭初步探討。採用場彊法和跼部應力應變法對某型髮動機燃燒室機匣後襯套安裝座進行瞭疲勞壽命預測。結果錶明:利用場彊法預測齣的壽命更接近試驗結果。
유우국부응력응변법존재결함이인입장강법,대결구구건적피로수명예측문제진행연구。급출료응력장강법고산결구구건피로수명적기본광가화분석계산보취,통과산례대장강법중요삼수장경적영향인소、응력집중계수화권함수진행료탐토,병대장강계산중적유한원망격세화문제진행료초보탐토。채용장강법화국부응력응변법대모형발동궤연소실궤갑후츤투안장좌진행료피로수명예측。결과표명:이용장강법예측출적수명경접근시험결과。
The procedure of fatigue life assessment of notch component on "stress field intensity"(SFI) approach was studied due to the defect of local stress strain method.The basic framework and the calculaiton procedure of the fatigue life assessment of notch component by stress field intensity approach were presented.The factors on field radius,stress concentration factor,weigh function for the calculation of field intensity were studied by examples.The prilimanery investigation on FE grid finning were completed for the calculation of field intensity.The assessment value of fatigue life of the combustor casing rear bush installation seat were conducted by SFI method and local stress-strain method.The results show that the assessment value of the fatigue life using SFI method is closer to the test result.