郑州轻工业学院学报（自然科学版）
鄭州輕工業學院學報（自然科學版）
정주경공업학원학보（자연과학판）
JOURNAL OF ZHENGZHOU INSTITUTE OF LIGHT INDUSTRY(NATURAL SCIENCE)
2015年
1期
81-84
,共4页
航空发动机%双辐板涡轮盘%换热边界%温度场%应力分布
航空髮動機%雙輻闆渦輪盤%換熱邊界%溫度場%應力分佈
항공발동궤%쌍복판와륜반%환열변계%온도장%응력분포
aero engine%twin-web turbine disk%heat transfer boundary%temperature field%stress distribution
基于ANSYS软件，研究了双辐板涡轮盘的温度场和应力场，通过划分各个区域的换热模型，较精确地计算了温度分布，再通过间接热－结构耦合计算出双辐板涡轮盘的应力分布．结果表明，双辐板涡轮盘最大平均径向应力、最大平均周向应力、盘心平均周向应力分别为702．35 MPa，679．68 MPa和880．98 MPa，不仅可满足规范设计要求的安全系数，还远小于材料的屈服强度1070 MPa，其结构完全满足了强度要求，并具有很大的发展空间．
基于ANSYS軟件，研究瞭雙輻闆渦輪盤的溫度場和應力場，通過劃分各箇區域的換熱模型，較精確地計算瞭溫度分佈，再通過間接熱－結構耦閤計算齣雙輻闆渦輪盤的應力分佈．結果錶明，雙輻闆渦輪盤最大平均徑嚮應力、最大平均週嚮應力、盤心平均週嚮應力分彆為702．35 MPa，679．68 MPa和880．98 MPa，不僅可滿足規範設計要求的安全繫數，還遠小于材料的屈服彊度1070 MPa，其結構完全滿足瞭彊度要求，併具有很大的髮展空間．
기우ANSYS연건，연구료쌍복판와륜반적온도장화응력장，통과화분각개구역적환열모형，교정학지계산료온도분포，재통과간접열－결구우합계산출쌍복판와륜반적응력분포．결과표명，쌍복판와륜반최대평균경향응력、최대평균주향응력、반심평균주향응력분별위702．35 MPa，679．68 MPa화880．98 MPa，불부가만족규범설계요구적안전계수，환원소우재료적굴복강도1070 MPa，기결구완전만족료강도요구，병구유흔대적발전공간．
The temperature field and stress field of the twin-web turbine were studied based on the ANSYS. Through dividing different parts of the turbine disk into different heat transfer model,the temperature field distribution was accurately calculated.And then the stress field distribution of the twin-web turbine disk was calculated by using the method of the indirect heat-structure coupling.The results showed that the maximum average radial stress,the maximum average circumferential stress and the average circumferential stress of plate heart were 702.35 MPa,679.68 MPa and 880.98 MPa,respectively.It not only met the re-quirement of the safety sactor,but also was less than the value of the yield strength,1 070 MPa.So the structure completely met the requirements of strength,and had the large development potential.
