Design of Two-Phase Injectors Using Analytical and Numerical Methods with Application to Hybrid Rockets

Niño, Emerson Vargas; Razavi, Mohammad R.

doi:10.2514/6.2019-4154

Cited by 1 publication

(3 citation statements)

References 29 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The excess pressure drop constant, K, is set to 2.28 for sharp-edge inlets [2]. The predicted value of C d with this relation is approximately 0.6 for liquid draining, which is reasonable and lies within the ranges indicated by Sutton [18].…”

Section: Resultssupporting

confidence: 66%

“…This section shows the comparison between the experimental average mass flow rate and the one predicted by the FML and Dyer's model. To make a meaningful comparison, the draining coefficient was computed through a semi-empirical relation based on the Reynolds number, the length to diameter ratio, and the sharp edge coefficient [2]. By applying the relation, the discharge coefficient is defined as:…”

Section: Resultsmentioning

confidence: 99%

“…Self-pressurizing propellants tend to flash across the orifice due to their high vapor pressure: this phenomenon leads to a two-phase fluid behavior along the downstream feeding line. Draining analyses have tried to reduce the problem through the implementation of equilibrium and non-equilibrium methods, as well as with new dedicated simulation frameworks [1,2]. Nowadays, one of the most used models for the prediction of the mass flow rate within self-pressurizing applications has been developed by Dyer [3].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A Two-Phase Mass Flow Rate Model for Nitrous Oxide Based on Void Fraction

Luna¹,

Foletti²,

Magni³

et al. 2022

Aerospace

View full text Add to dashboard Cite

In the field of space propulsion, self pressurized technology is an example of innovation capable of improving system performances through reduction of volumes and other optimizations. Potential applications are widespread and not limited to the propulsion panorama: from on-orbit maneuvering to in-orbit servicing, from refueling of satellites at the end of life to in situ resource exploitation for missions headed towards remote objects of the solar system. However, important drawbacks have been reported for these systems: modeling of fluids and thermal phenomena is complex, thus preventing accurate performance predictions. As a result, no comprehensive and accurate model capable of describing the dynamics of a self-pressurizing propellant tank has been developed so far. In this context, this paper proposes a two-phase mass flow rate model based on void fraction. N2O has been selected due to its use as a green and self-pressurized propellant for in-space propulsive applications. The aim of this paper is to describe the current mass flow rate models present in the literature for this fluid and compare the new model with the one proposed by Dyer. A model validation is also offered, and a test campaign is mentioned. Finally, preliminary results are shown and discussed: results are then compared with the ones obtained through the Dyer model, in order to retrieve a comprehensive comparison among the two simulation frameworks. Comments on the results are added, showing the improvements as well as the limitations of the proposed framework.

show abstract

Section: Resultssupporting

confidence: 66%

Section: Resultsmentioning

confidence: 99%