Design and performance analysis of an exhaust system for an over-under turbine based combined cycle operating at Mach 0–6
Design and performance analysis of an exhaust system for an over-under turbine based combined cycle operating at Mach 0–6
复制标题
0-6马赫下基于涡轮的联合循环排气系统的设计和性能分析
DOI：
10.1016/j.ast.2019.105386
复制
发表时间：
2019-11
影响因子：
5.6
通讯作者：
Song Guangtao
中科院分区：
文献类型：
--
作者：
Lv Zheng;Xu Jinglei;Song Guangtao
The present study focuses on the design and performance analysis of an exhaust system for an over-under turbine based combined cycle (TBCC) operating at Mach 0–6. The computational fluid dynamics (CFD) approach is employed to obtain the flowfield and performance of the exhaust system. The single expansion ramp nozzle (SERN) considering geometric constraints at the cruise condition is designed by a new method based on maximum thrust theory, and the initial expansion angle on the cowl is set at 0.37 rad. The lower cowl is sliding as well as rotating around a fixed point to satisfy the adjustment requirement of the high-speed flowpath, and shifting the location of the fixed point forward has a positive effect on the performance of the exhaust system. In order to eliminate the adjustment interaction between the low-speed and high-speed flowpaths and decreases the expansion ratio of the low-speed flowpath, the splitter location is shifted backward, and the optimal location and top contour angle of the splitter are set to 220 mm and 20°, respectively. The flowfield structure is relatively simple at the separate operation, while it is obviously complex at the parallel operation, with the flow interaction between the turbine exhaust jet and rocket ejector plume. With the increase in the flight Mach number, the axial thrust coefficient is increased rapidly at the separate operation of the turbine, while it increases firstly and then decreases at the parallel operation. For the separate operation of the high-speed flowpath, the axial thrust coefficient maintains above 0.96 and also increases firstly and then decreases gradually as the increase in the flight Mach number.
登录
查看更多内容
影响因子：
5.6
作者：
黄伟;颜力;谭建国
通讯作者：
谭建国
DOI：
10.2514/6.1994-2949
发表时间：
1994-06
期刊：
--
影响因子：
--
作者：
Ing Chang;L. Hunter
通讯作者：
Ing Chang;L. Hunter
影响因子：
3.5
作者：
Shuaitao Guo;Jinglei Xu;J. Mo;Rui Gu;L. Pang
通讯作者：
Shuaitao Guo;Jinglei Xu;J. Mo;Rui Gu;L. Pang
DOI：
10.1115/1.4025314
发表时间：
2014
期刊：
Journal of engineering for gas turbines and power
影响因子：
--
作者：
J. Mo;Jinglei Xu;Liuhuan Zhang
通讯作者：
J. Mo;Jinglei Xu;Liuhuan Zhang
影响因子：
3.5
作者：
Zheng Lv;Jinglei Xu;J. Mo
通讯作者：
Zheng Lv;Jinglei Xu;J. Mo