TSPR涡轮增压器出口方式对掺混燃烧的影响  

Influence on afterburning efficiency by TSPR turbocharger's exhausted gas's flowing methods

作　　者：李江[1] 刘诗昌[1] 王伟[1] 刘洋[1] 刘凯[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2017年第1期24-31,51,共9页Journal of Solid Rocket Technology

摘　　要：针对涡轮增压器出口气流进入涡轮增压固冲发动机(Turbocharged Solid Propellant Ramjet,TSPR)补燃室后,因同轴流动而造成掺混燃烧效率不高的问题,通过对比研究ATR(Air Turbocharged Ramjet)及固冲发动机掺混燃烧增强手段,形成了一种可有效增强TSPR补燃室掺混燃烧效果的方案。继而通过数值模拟的手段对该方案的有效性和内在机理进行了讨论。最后通过TSPR工作模式的数值模拟,发现在不同富燃燃气余气系数状态下补燃室效率均能保持90%以上,验证了该方案的有效性和适用性。根据这些研究,该文认为保留驱涡燃气高速旋流配合增压空气采用一定射流角度进入燃烧室的出口流动方式能够使TSPR补燃室有效工作,燃烧效率相对原有ATR模式能够提高1倍以上;其中涡轮的旋转速度高于40 000 rpm时,经过涡轮膨胀做功的驱涡燃气使发动机比冲和补燃室温度分布情况都比较理想;增压空气采用40°~50°的射流角进行斜向射流对发动机比冲性能提高和补燃室内温度分布改善是比较有利的。By studying the afterburning of the TSPR（Turbocharged Solid Propellant Ramjet）,it was found that efficient combustion was difficult to be achieved when the exhaust,from turbocharger,flew into afterburner coaxially.Based on that,by comparative study of ATR（Air Turbocharged Ramjet） and SRM（Solid Ramjet Motor） afterburning enhancement technology,an effective method to enhance TSPR afterburning efficiency was established.Then,by means of numerical simulation,the effectiveness and internal mechanism for these enhancement technologies were discussed.Finally,the TSPR mode was examined by the simulation method,and it was found that the afterburning efficiency could keep more than 90% in various fuel-rich gas flow rate,which verified the validity and the applicability of the enhancement method.According to those studies,it is suggested to be an effective way for the afterburning that to keep the rotation speed of the driving-turbo gas and to make the pressurized air jet in some special angle,and the combustion efficiency could reach as high as twice of the experimental combustion efficiency working in formal method.Specifically,when the rotation speed was no less than 40 000 rpm,the driving-turbo gas could make TSPR＇s ISP and combustor＇s temperature distribution desirable.When the pressurized air＇s jet angle was between 40° ～ 50°,it is favorable to the enhancement of TSPR＇s ISP and combustor＇s temperature distribution.

关 键 词：涡轮增压固冲发动机 涡轮增压 补燃室 掺混燃烧 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]