Abstract Rocket-ejector system as a pressurization unit is of critical importance to the rocket-based combined-cycle engine under the low flight Mach number conditions. Due to the restriction of engine scale, an insufficient mixing process exists in the limited mixer length, leading to a non-uniform stream at the mixer exit. This study concentrated on hot-fire tests to demonstrate the flow characteristics of the rocket-ejector system with the limited mixer length. The results show that shortening the length reduces the critical backpressure of the rocket-ejector system. The rocket-ejector system with a mixer length of 6 length-to-diameter ratio to the straight section can resists the critical pressure ratio of 1.25 in which the entrainment coefficient is 3.432, the total pressure ratio is 36.4 and the occupied area ratio of the rocket exit to the straight section is about 32%. Although the non-uniformity of mixed stream at the mixer exit section would reduce the critical pressure to some extent, the limited mixer length also meet the operation requirements of the rocket-based combined-cycle engine with the diffusion and afterburning cycle.
Highlights Hot-fire tests were carried out to demonstrate the flow characteristics of the rocket-ejector system. The rocket-ejector system performances under different back pressures and mixer lengths conditions were revealed. The limited mixer length may meet the operation requirements of the RBCC engine with the DAB cycle.
Numerical modeling and experimental investigation on the rocket-ejector system with limited mixer length
Acta Astronautica ; 182 ; 13-20
2021-01-24
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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