Influence of oncoming flow parameters on rotating detonation combustor with supersonic turbine guide vanes

• Main Authors: Wen, Fengbo, Su, Liangjun, Wang, Ying, Han, Jiajun, Wang, Songtao
• Other Authors: School of Mechanical and Aerospace Engineering
• Format: Article
• Language: English
• Published: 2024
• Subjects: Engineering; Detonation waves; Flow parameters
• Online Access: https://hdl.handle.net/10356/178346
• Institution: Nanyang Technological University

Rotating detonation combustion can greatly improve the performance of air-breathing turbojet engines due to its self-pressurization and high combustion efficiency. Detonation wave propagation is closely related to oncoming flow parameters. The supersonic turbine guide vane plays a role in weakening the uneven oscillation caused by the propagation of the detonation wave. Therefore, the study of the influence of oncoming flow parameters on the coupling between the rotating detonation combustor and the supersonic turbine plays a key role in the design of the rotating detonation supersonic turbine engine. In this paper, we study the influence of oncoming flow parameters ( A w / A t ∼ 25-15, P 0 ∼ 0.5-1.5 MPa, T 0 ∼ 250-350 K, p b ∼ 0.5-1.5 atm, and Φ ∼ 0.6-1.4) and propagation direction (D ∼ R-L) on the performance and flow mechanism of the coupling of a rotating detonation combustor with supersonic turbine guide vanes; a total of 27 cases are calculated and analyzed. According to the study, the injection parameters mainly determine the premixed fuel injection flow rate and its physical and chemical characteristics, thereby affecting the secondary detonation of the detonation wave. The detonation wave will exhibit four propagation modes: single wave mode, multi-wave mode, multi-wave co-propagation mode, and multi-wave reverse-propagation mode. The formation of multi-wave modes is the result of multi-wave collision, annihilation and secondary detonation of detonation waves. Under different parameter conditions, the intensity of the secondary detonation is different. The single wave mode is due to the low stoichiometric ratio and low total temperature inhibiting the secondary detonation. As for the reverse propagation mode and multi-wave collision, multi-wave co-propagation is caused by the interaction between the new detonation wave caused by the secondary detonation and the detonation wave. The interaction between rotating detonation and supersonic turbine guide vanes is mainly reflected in the interaction between oblique shock waves and supersonic turbine guide vanes, which will generate basic wave structures such as channel shock waves, reflected shock waves, and dovetail waves. The interaction area between the slip lines and the oblique shock waves and the guide vanes of the supersonic turbine will form local high temperature zones, resulting in a large local thermal load. These laws provide reference for the coupling design of rotating detonation and supersonic turbine.