涡轮导向器喉道尺寸对燃气涡轮起动机性能的影响  

Effect of throat size of turbine guide on performance of gas turbine starter

作　　者：樊小倩 汪洋冰 刘一鸣 白杰 FAN Xiaoqian;WANG Yangbing;LIU Yiming;BAI Jie(Jincheng Nanjing Engineering Institute of Aircraft Systems,Aviation Industry Corporation of China,Limited,Nanjing 211106,China;Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration,Aviation Industry Corporation of China,Limited,Nanjing 211106,China)

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

出　　处：《航空动力学报》2024年第9期140-148,共9页Journal of Aerospace Power

基　　金：集团创新专项(YY20012-02)。

摘　　要：以某燃气涡轮起动机的燃气涡轮导向器为研究对象,采用试验及数值模拟方法研究了燃气涡轮导向器喉道尺寸对燃气涡轮起动机整机及部件性能的影响。针对A、B、C型三种燃气涡轮导向器(喉道平均外径分别为111.27、111.94、112.34 mm)的试验研究结果表明:C′型燃气涡轮起动机较A′型燃气涡轮起动机,正常起动时间缩短14%,失效起动输出轴脱开转速升高7.1%,最大输出功率增加11.6%,起动机性能显著提高。数值结果表明:C″型较A″型涡轮级流量增加3.6%,动力涡轮最大输出功率增加12.2%,动力涡轮功率增加归因于流量增加、温度增加、温降增加的叠加效应。总之,燃气涡轮导向器喉道外径通过影响涡轮级性能改变了燃气涡轮起动机整机的匹配特性,使整机性能存在一定的分散性。A gas turbine guide on a gas turbine starter was taken as the research object,and the effects of throat size of gas turbine guide on the performance of gas turbine starter and components were studied using experimental methods and numerical simulation.The results of experimental research on A,B,C types of gas turbine guide(average outer diameter of the throat was 111.27,111.94,112.34 mm)indicated:type C′starter compared with type A′starter,normal starting time became shorter by 14%,output shaft disengagement speed of lose efficacy starting increased by 7.1%,maximum output power increased by 11.6%,the performance of starter was improved significantly.Numerical research results indicated:type C″compared with type A″,the flow rate of turbine stage increased by 3.6%,maximum output power of power turbine increased by 12.2%.The increase in power turbine power was attributed to the combined effect of increased flow rate,increased temperature and increased temperature drop.In summary,the outer diameter of gas turbine guide throat changed the matching point of entire gas turbine by affecting the performance of turbine stage,then the overall performance exhibited a certain degree of dispersion.

关 键 词：燃气涡轮起动机 涡轮导向器 喉道尺寸 外径 动力涡轮 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]