离心叶轮圆钝型叶片前缘对燃气涡轮起动机性能的影响  

Influence of Circular Blunt Leading Edge of Centrifugal Impeller Blade on Performance of Gas Turbine Starter

在线阅读下载全文

作  者:樊小倩 黄松 白杰 朱家桢[1,2] FAN Xiaoqian;HUANG Song;BAI Jie;ZHU Jiazhen(AVIC Jincheng Nanjing Electromechanical and Hydraulic Engineering Research Center,Nanjing,China,211106;Key Laboratory of Integrated Aviation Science and Technology of Aviation Electromechanical System of AVIC,Nanjing,China,211106)

机构地区:[1]中国航空工业集团公司金城南京机电液压工程研究中心,江苏南京211106 [2]中国航空工业集团公司航空机电系统综合航空科技重点实验室,江苏南京211106

出  处:《热能动力工程》2024年第10期76-85,共10页Journal of Engineering for Thermal Energy and Power

基  金:中国航空工业集团创新专项(YY20012-02)。

摘  要:本文以某燃气涡轮起动机的离心叶轮为研究对象,首先采用试验方法研究了加工导致的圆钝型叶片前缘(圆弧过度的钝头前缘)形状对燃气涡轮起动机整机性能的影响,进一步采用CFD数值仿真方法对原模型(Ⅰ型)及两种圆钝型前缘(Ⅱ型、Ⅲ型)离心压气机部件的性能进行了对比研究。研究结果表明:离心叶轮叶片的圆钝型前缘使起动机整机的正常起动时间增加11.6%,失效起动输出轴脱开转速降低10.7%,最大输出功率减小16.8%,起动机性能显著下降;圆钝型叶片前缘导致压气机的堵塞流量下降,最高压比下降,峰值效率下降,主要归因于离心叶轮叶片附面层损失及尾缘流动损失增大。Taking the centrifugal impeller used on a gas turbine starter as research object,experimental methods were used firstly to study the influence of circular blunt leading edge(blunt leading edge with excessive arc)shape due to processing on the overall performance of gas turbine starter.Further analysis was conducted using CFD numerical simulation to compare the performance of the original model(model I)and two types of circular blunt leading edges(model I,model II)centrifugal compressors.The research results indicate that centrifugal impeller blade with circular blunt leading edge increases the nor-mal starting time of the starter by 11.6%,reduces output shaft disengagement speed of defunct starting by 10.7%,reduces maximum output power by 16.8%,the performance of starter is degraded signifi-cantly;and the circular blunt leading edge reduces the blocking flow,the maximum pressure ratio and the peak efficiency of compressor.The main reason is the increase in boundary layer loss and flow loss at the trailing edge of the centrifugal impeller blade.

关 键 词:燃气涡轮起动机 离心叶轮 前缘形状 圆钝型 输出功率 

分 类 号:V231.3[航空宇航科学与技术—航空宇航推进理论与工程]

 

参考文献:

正在载入数据...

 

二级参考文献:

正在载入数据...

 

耦合文献:

正在载入数据...

 

引证文献:

正在载入数据...

 

二级引证文献:

正在载入数据...

 

同被引文献:

正在载入数据...

 

相关期刊文献:

正在载入数据...

相关的主题
相关的作者对象
相关的机构对象