Isentropic Compressible Flow for Non-Ideal Gas Models for a Venturi

Cornelius, Kenneth C.; Srinivas, Kartik

doi:10.1115/1.1677499

Cited by 6 publications

(6 citation statements)

References 6 publications

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“…When the flow is choked, and then independent of downstream pressure fluctuations, the maximum flow rate through the injector is provided by Eq. 4. where is included the compressibility factor z appearing in the mechanical equation of state for real gas [20].…”

Section: Single Phase Compressible (Spc)mentioning

confidence: 99%

Review and perspectives of “Green” Self-Pressurizing Propellants for In-Space Propulsion and their applicability to Orbital Stages

Sarritzu,

Pesante,

La Luna

et al. 2024

AIAA SCITECH 2024 Forum

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Green Propulsion is an increasingly prevalent trend in the space industry that has experienced significant growth in recent decades. The shared objective of researchers is to identify suitable alternatives to existing liquid propellants for space applications, which are toxic and difficult to manage during ground operations. Research and industry have explored a wide range of options and, especially in the last few years, there has been a clear push from the market and the overall space sector to utilize cheaper and simpler systems. Numerous alternatives are emerging as advantageous for a variety of applications. Green propellants are typically utilized for in-space propulsion applications that necessitate high thrust and short transfer durations and over the years, around the world, researchers and industries have tested dozens of different propellants. Recently there is an increased interest in exploiting a particular characteristic of some compounds, the so-called self-pressurization, i.e. the property of compounds with a high vapor pressure at conventional operating temperatures of possessing an inherent feeding pressure. The principal advantage of systems based on these propellants is their self-pressurizing capability, which eliminates the need for external pressurization sub-systems, resulting in simpler and more compact designs. The present study evaluates the relative performance of many of these compounds as propellants for an Orbital Stage reference scenario.

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Section: Single Phase Compressible (Spc)mentioning

confidence: 99%

Review and perspectives of “Green” Self-Pressurizing Propellants for In-Space Propulsion and their applicability to Orbital Stages

Sarritzu,

Pesante,

La Luna

et al. 2024

AIAA SCITECH 2024 Forum

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show abstract

“…For compressible liquids or real gases, the correction factor should be calculated in the same fashion of Zimmerman et al [13]. It is based upon the non-ideal gas flow power law theory of Cornelius and Srinivas [14]. This form of the compressible liquid correction factor, Y , is outlined in Equation (7).…”

Section: Single Phase Compressiblementioning

confidence: 99%

“…This form of the compressible liquid correction factor, Y , is outlined in Equation (7). It is also valid for injectors but only under the assumption of isentropic flow through it [14]:…”

Section: Single Phase Compressiblementioning

confidence: 99%

See 1 more Smart Citation

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

Luna¹,

Foletti²,

Magni³

et al. 2022

Aerospace

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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.

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“…In Ref. 16, equations for the flowrate of non-ideal gases through a venturi are developed. For isentropic flows,ṁ…”

Section: Appendix A: Details Of Experimental Setupmentioning

confidence: 99%

Initial Experimental Investigations of Self-Pressurizing Propellant Dynamics

Zimmerman

Cantwell²,

Zilliac³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Hybrid rockets commonly use nitrous oxide as a self-pressurizing oxidizer, but no comprehensive models exist for predicting the performance of such a system. To aid in the development of such a model, an experimental apparatus has been constructed with a transparent cylinder that allows for optical measurements as well as pressure, temperature, and mass flowrate measurements. Carbon dioxide has been identified as an analog for nitrous oxide, facilitating laboratory-scale testing. Initial results of tests with this system show that there is significant boiling within the liquid and that the propellant is not maintained in thermodynamic equilibrium. Furthermore, both supercharge configuration and mass flowrate strongly affect the dynamics of self-pressurizing propellants.

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Isentropic Compressible Flow for Non-Ideal Gas Models for a Venturi

Cited by 6 publications

References 6 publications

Review and perspectives of “Green” Self-Pressurizing Propellants for In-Space Propulsion and their applicability to Orbital Stages

Review and perspectives of “Green” Self-Pressurizing Propellants for In-Space Propulsion and their applicability to Orbital Stages

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

Initial Experimental Investigations of Self-Pressurizing Propellant Dynamics

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