Evaporation of Three-Dimensional Wavy Liquid Film Entrained by Turbulent Gas Flow

Inoue, Takeshi; Inoue, Chihiro; Fujii, Go; Daimon, Yu

doi:10.2514/1.j061381

Cited by 12 publications

(1 citation statement)

References 40 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The sequential phenomena inside a bipropellant thruster involve the injection of fuel and oxidizer jet streams, spray formation by unlike impingement of the jets [14,15], mixing in the spray, condensed-phase reactions, droplet evaporation, gas-phase reactions, and production of combustion gas [16][17][18]. Simultaneously, the film-cooling technique is used to protect the chamber wall from hot combustion gas by the latent heat of the liquid fuel film spreading on the inner wall, and eventually self-decomposing [19][20][21]. The complex multi-phase thermo-fluid dynamics of these processes have necessitated time and cost consuming combustion tests for performance measurements.…”

Section: Introductionmentioning

confidence: 99%

Unsteady Stream-Tube Model for Pulse Performance of Bipropellant Thrusters

Oishi

Tauchi

Inoue

2023

Journal of Propulsion and Power

Self Cite

View full text Add to dashboard Cite

We propose a theoretical model for predicting the impulse bit of bipropellant thrusters under pulse-firing operations. The present theoretical model, which considers the nonuniformity of the mixture ratios created inside the thrust chamber, extends the stream-tube approach, which is limited to the prediction of the steady performance. In pulse-firing operation, the fuel or the oxidizer alone can be injected in isolation due to the mismatched injection timing before the rated injection, which leads to the deterioration of performance as compared with the steady operation. The present approach (the unsteady stream-tube model) successfully implements a time-dependent stream-tube structure inside the thrust chamber, allowing for the prediction of the impulse bit as a straightforward function of the injection conditions. Three different pulse-firing tests using distinct hypergolic propellants demonstrate the validity of this model, typically reproducing the notable trend of deterioration in the impulse bit in the short-pulsed mode. We also examine the time-averaged specific impulse and mass flow rate to improve the impulse bit during short-pulsed operations.

show abstract