摘要
为提高涡轮钻具叶片使用性能和创新叶片设计理论,提出了基于儒可夫斯基保角变换法与经典水力翼型相结合的涡轮钻具叶片设计新方法,以?127涡轮钻具叶片为研究对象,运用搭建的涡轮钻具叶型参数化设计平台和自主设计的涡轮钻具性能测试台架,完成了5种翼型的造型设计,研究了5种叶片流场性能,开展了设计叶片的性能测试实验,对比分析了设计叶片与塔里木油田某型在役?127涡轮叶片的实际效能。实验及仿真结果表明,基于新方法设计的NACA-0012翼型加厚叶片在600 r/min转速及15 L/s流量的设计工况下,其单级扭矩达5.83 N·m,较相同条件下某在役?127涡轮的单级扭矩提高约6.4%,级效率提高约1.16%,整体性能有了实质提升。
In order to improve the performances of turbodrill blades and to innovate blade design theory,a new method of turbodrill blade design was proposed based on the combination of Joukowski conservative angle transform airfoil design theory and the classic hydraulic airfoil.Taking ?127 turbodrill blade as research object,5 kinds of ?127 turbodrill airfoil design were completed by using built turbodrill blade parametric design platform and self-designed turbodrill performance test bench.The flow characteristics corresponding to 5 kinds of blade were discussed in detail.Then the performance tests of the designed blades were carried out.Finally,actual performances of the design airfoils and a ?127 turbine blade serving in Xinjiang Tarim Oilfield were compared and analyzed.The experimental and simulation results show that single-stage torque of NACA-0012 type thickened blades which are designed based on a new method reaches 5.83 N·m under the test conditions of 600 r/min rorate speed and 15 L/s flow rate.Comparing with the ones serving in Xinjiang Tarim Oilfield under the same conditions,single stage torque increases 6.4%and stage efficiency increases 1.16%,which show overall performance improvements.
作者
张晓东
林梦
龚彦
郝仁杰
杨林
ZHANG Xiaodong;LIN Meng;GONG Yan;HAO Renjie;YANG Lin(School of Mechanical Engineering,Southwest Petroleum University,Chengdu,610500)
出处
《中国机械工程》
EI
CAS
CSCD
北大核心
2020年第8期968-974,共7页
China Mechanical Engineering
基金
国家重点研发计划资助项目(2018YFC0310201)。
