Numerical Modeling of Pressurization of a Propellant Tank

Majumdar, Alok; Steadman, Todd

doi:10.2514/2.5754

Cited by 38 publications

(13 citation statements)

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“…Ideally speaking, the pressurizing gas should not condense or be soluble into the liquid propellants and, thus, the helium gas would be the best choice for pressurizing the propellant tanks. In this way, the pressurization system controls the gas pressure in the gas space of the propellant tanks or ullage and maintains this ullage at a predetermined pressure required by propellant and structural requirements of tanks [10,11].…”

Section: Introductionmentioning

confidence: 99%

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Kim

et al. 2012

J. Engin. Thermophys.

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The transient thermal behavior in the cryogenic oxidizer tank for the liquid propulsion system of the KSLV-I satellite launching space vehicle is theoretically investigated for the pressurization process by gaseous helium injection followed by the readiness check stage. The numerical model is established using the transient mass and energy conservation of oxygen/helium mixtures both in ullage and liquid regions. At the liquid-gas interface, various modes of heat and mass transfer are considered, including the liquid evaporation and the helium absorption. The present study focuses on the effects of the increasing pressurization level on some of important properties that should be considered in the propulsion system design, such as tank pressure, ullage gas temperature, and evaporation of liquid oxygen. Particularly, the tank pressure drop after the pressurization is investigated in the proposed design of propulsion system. Also, the effect of the initial loading of liquid oxygen in the oxidizer tank is studied and discussed. As for the helium absorption into the liquid region, its mass is negligibly small and it should not be the concern in design and operation of the oxidizer tank system.

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Section: Introductionmentioning

confidence: 99%

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Kim

et al. 2012

J. Engin. Thermophys.

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“…The tank geometry and instrumentation for the demonstration tanks and the geometry of the full-scale tank has been described. The details of the three numerical models described in section 1.2 have been described in section 4. The results of all three numerical models are described in section 5.…”

Section: Outline Of the Reportmentioning

confidence: 99%

“…The Generalized Fluid System Simulation Program (GFSSP), developed at MSFC, 3,4 has been used to develop the thermal models for estimating boiloff in the demonstration tanks and the liquid hydrogen storage tank at LC-39. GFSSP is a finite volume-based computer code for analyzing fluid flow in a complex flow circuit.…”

Section: Numerical Approachmentioning

confidence: 99%

“…GFSSP already contains a pressurization option, which considers the interaction between the ullage and liquid in a propellant tank. 4 This pressurization option was adapted to model the fluid portion of the boiloff model by including the capability to calculate spherical geometrical parameters such as volumes, heights, and surface areas. These spherical geometry calculations are discussed in appendix C. Because the pressurization option is a transient option, the model was run in a transient mode of operation, where time step represented an additional iterative step to achieve steady state convergence.…”

Section: Ullage and Propellant Node Tank Modelmentioning

confidence: 99%

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Numerical Modeling of Propellant Boil-Off in a Cryogenic Storage Tank

Majumdar

Steadman

Maroney

et al. 2008

AIP Conference Proceedings

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“…GFSSP is a robust general fluid system analyzer, based on the finite volume method, with the capability to handle phase change, heat transfer, chemical reaction, rotational effects, and fluid transients in conjunction with subsystem flow models for pumps, valves, and various pipe fittings. [4] GFSSP has been extensively verified and validated by comparing its predictions with test data and other numerical methods for various applications, such as internal flow of turbo-pumps, [5] propellant tank pressurization, [6,7] and squeeze film damper rotordynamics. [8] GFSSP has also been used to predict the chilldown of a cryogenic transfer line, based on transient heat transfer effects and neglecting fluid transient effects.…”

Section: Introductionmentioning

confidence: 99%

Numerical Modeling of Thermofluid Transients During Chilldown of Cryogenic Transfer Lines

Majumdar¹,

Steadman²

2003

SAE Technical Paper Series

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This paper describes the application of a finite volume procedure for a fluid network to predict thermofluid transients during chilldown of cryogenic transfer lines. The conservation equations of mass, momentum, and energy and the equation of state for real fluids are solved in a fluid network consisting of nodes and branches. The numerical procedure is capable of modeling phase change and heat transfer between solid and fluid. This paper also presents the numerical solution of pressure surges during rapid valve opening without heat transfer. The numerical predictions of the chilldown process have been compared with experimental data.

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Numerical Modeling of Pressurization of a Propellant Tank

Abstract: ABSTRACT

Cited by 38 publications

References 1 publication

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Numerical Modeling of Propellant Boil-Off in a Cryogenic Storage Tank

Numerical Modeling of Thermofluid Transients During Chilldown of Cryogenic Transfer Lines

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