Prof. Feilong Song

Air Force Engineering University, China

E-mail: fl_song1992@163.com

Bio

Song Feilong, Ph.D., is an Associate Professor at Air Force Engineering University. His research focuses on turbine-based rotating detonation engine (RDE) combustor operating characteristics and engine integration matching. He has presided six projects, including the National Natural Science Foundation of China's Youth Science Fund (Category C) and general projects, as well as military and provincial-ministerial-level projects such as the Air Force Equipment Pre-research Program.
Dr. Song achieved breakthroughs in detonation wave pressure feedback suppression and propagation mode control, substantially improving the total pressure recovery coefficient of the RDE combustor. The first domestic whole-engine verification of an RDE afterburner integrated with a single-shaft turbojet engine at 100 kgf and 400 kgf thrust levels was completed. He has published 17 SCI papers in journals such as Combustion and Flame and Aerospace Science and Technology, holds 13 invention patents, and serves as a reviewer for these journals and as a youth reviewer for the Scientific Core Evaluation Database.
His honors include the First Prize of Shaanxi Provincial Science and Technology Progress Award (2024), the First Prize of Military Science and Technology Progress Award (2020), the Shaanxi Excellent Doctoral Dissertation Award, and the Aviation Power Chinese Heart Innovation Award. He was selected for the Young Elite Scientists Sponsorship Program (CAST), the Military High-Level Innovation Talent Program (Young Scientific and Technological Talent), and the University’s Young Sprout Talent Program.

Title

Research on Feedback Suppression and Intake Control for Rotating Detonation Combustor

Abstract

Rotating detonation combustion offers advantages such as high thermal efficiency, rapid heat release, and self-pressurization. Propulsion concepts centered on detonation combustion are considered one of the key pathways to overcome the technical limitations of current air-breathing engines, demonstrating significant application potential.
To address the requirements for wide operating range adaptability in turbine-based rotating detonation afterburner chambers and the challenge of matching turbines with afterburners, research has been conducted on detonation wave feedback suppression and inlet flow control. A Tesla-valve-inspired aerodynamic configuration for rotating detonation combustors has been proposed, achieving breakthroughs in suppressing pressure feedback from detonation waves and controlling their propagation modes. Additionally, an adjustable throat geometry design for the inlet has been developed, revealing the mechanisms by which hysteresis caused by detonation waves leads to deviations in total pressure recovery and combustion efficiency.