Analysis of flow field of three-dimensional ejector nozzle with open-close alternate intake valve at transonic velocity

被引：0
|
作者：
Li Z. [1 ]
Wang H. [1 ]
Huang H. [2 ]
机构：
[1] School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing
[2] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 12期
关键词：
ejector nozzle; open-close alternate intake valve; thrust performance; transonic speed; vortex;
D O I：
10.13224/j.cnki.jasp.20210581
中图分类号：
学科分类号：
摘要：
To analyze the influence of different secondary air intake states, the flow characteristics of an ejector nozzle with open-close intake valves in the transonic flight state (Ma=1.2) were simulated and studied. By changing the nozzle pressure ratio (NPR) of the secondary flow, the flow state of the third flow, the development characteristics of the vortex, and the thrust performance in the nozzle were analyzed. The results showed that the airflow in the ejector nozzle with the open-close alternate intake valve had the phenomenon of lateral flow, forming a vortex ring that the size of the flow vortex gradually decreased along the flow direction. The main flow maintained an over-expansion state, which dominated the inner flow of the ejector nozzle, and formed a shear layer structure with the secondary flow. With the increase of the NPR of the secondary flow, the flow rates of the secondary and third flows increased, which led to a stronger binding effect on the main flow. Therefore, the mainstream over-expansion phenomenon was effectively suppressed, so the thrust performance increased from 0.698 to 0.819. © 2023 BUAA Press. All rights reserved.
引用
收藏
页码：2937 / 2947
页数：10
相关论文
共 18 条
  • [1] (1998)
  • [2] TAKAHASHI M，, SUNAMI T, Et al., Performance characteristics of a scramjet engine at Mach 10 to 15 flight condition, (2005)
  • [3] HEISER W H., Ejector thrust augmentation, Journal of Propulsion and Power, 26, 6, pp. 1325-1330, (2010)
  • [4] WILSON J, SGONDEA A, PAXSON D E, Et al., Parametric investigation of thrust augmentation by ejectors on a pulsed detonation tube, Journal of Propulsion and Power, 23, 1, pp. 108-115, (2007)
  • [5] VIETS H., Thrust augmenting ejector analogy, Journal of Aircraft, 14, 4, pp. 409-411, (1977)
  • [6] CANDEL S., Concorde and the future of supersonic transport, Journal of Propulsion and Power, 20, 1, pp. 59-68, (2004)
  • [7] ZHANG Xianfeng, LIU Minghou, ZHANG Gen, Et al., Simulations of flow field and thrust performance in micronozzle, Journal of Astronautics, 27, 4, pp. 720-725, (2006)
  • [8] DEBONIS J., Full Navier-Stokes analysis of a two-dimensional mixer/ejector nozzle for noise suppression, (1992)
  • [9] CHOW W L，, ADDY A L., Interaction between primary and secondary streams of supersonic ejector systems and their performance characteristics, AIAA Journal, 2, 4, pp. 686-695, (1964)
  • [10] JOE D, Improved methods of characterizing ejector pumping performance, Journal of Propulsion and Power, 7, 3, pp. 412-419, (1991)
12