Analysis of mixing enhancement ability of bypass dual throat nozzle with single/multi-tabs

Abstract

Bypass dual throat nozzle (BDTN) represents an innovative fluidic thrust vectoring nozzle capable of adjusting thrust vectoring angles through self-adaptive flow control. This study explores the BDTN-single/multi-tabs configurations, ensuring that the nozzle’s outlet projected area remains constant while introducing one or more pairs of tabs coplanar with the convergent section of the cavity. This design accounts for aerodynamic performance, thrust vectoring capabilities, and mixing abilities of the BDTN. Through theoretical analysis, design implementation, numerical simulations, and wind tunnel experiments, findings reveal that, in the case of BDTN-single-tab configuration, an increase in tab angle (α) leads to heightened streamwise vortex intensity at the nozzle outlet, reduced high-temperature core area, and enhanced jet centerline velocity and temperature attenuation rate. BDTN-single-tab achieves up to a 90% reduction in centerline-temperature/velocity decay rate, implying stronger mixing enhancement with higher tab angles. Compared to α = 10° BDTN-single-tab, the area of the high-temperature core area decays by 75%. For the BDTN-multi-tab configuration, an increase in the number of tabs results in increased thrust coefficient and vectoring angle, alongside diminished streamwise vortex strength at the nozzle outlet, and a more complex streamwise vortex structure. However, the jet’s centerline velocity and temperature decay rate decreased as a consequence.

Disclosure statement

No potential conflict of interest was reported by the author(s).

Additional information

Notes on contributors

Ruifeng Pan

Ruifeng Pan is currently working toward a Ph.D. degree in Power Engineering and Engineering thermophysics in College of Energy and Power Engineering at Nanjing University of Aeronautics and Astronautics. He received his master’s degree from Nanjing University of Aeronautics and Astronautics. His research interest is flow control with fluidic thrust vectoring nozzle in the field of future fighters. He has applied for more than 20 invention patents in related fields. He has received the 4th International Symposium of Thermal-Fluid Dynamics (ISTFD) Best Paper Award.

Jinglei Xu

Jinglei Xu is a Professor at Nanjing University of Aeronautics and Astronautics. He obtained his Ph.D. in Fluid Machinery and Engineering from Xi’an Jiaotong University in 1999. He has received several prestigious awards such as the second prize for National Science and Technology Progress of China and the gold medal at the Geneva International Invention Exhibition. His research interests include engine internal flow aerodynamics, propulsion systems for hypersonic aircraft, and wind tunnel experimental technology. He has published more than 180 papers, including over 70 SCI papers and 2 monographs. He has been a member of the Engine Soft Science Professional Committee of the Chinese Aeronautical Society, the chair of the 4th ISTFD, an AIAA senior member and an ASME member in the United States.

Yuqi Zhang

Yuqi Zhang is a Ph.D. student at Nanjing University of Aeronautics and Astronautics. Her research mainly focuses on internal flow aerodynamics. She has published two SCI papers, and she is the first author of one SCI paper.

Bingsong Lan

Bingsong Lan graduated from the School of Energy and Power of Nanjing University of Aeronautics and Astronautics with a bachelor’s degree in 2022 and entered Nanjing University of Aeronautics and Astronautics to pursue a doctoral degree, mainly engaged in the research of fluid thrust vector nozzle.

Shuai Huang

Shuai Huang is an Assistant Professor at Nanjing University of Aeronautics and Astronautics. His main research field includes flow control, novel fluidic thrust vectoring nozzle, short/vertical take-off and landing propulsion of aircraft, and new concept propulsion systems. He has obtained more than 40 patents and published more than 10 papers. He is the main recipient of the gold medal of the Geneva International Invention Exhibition.