Cryogenic Fluid Management Technologies for Advanced Green Propulsion Systems

Motil, Susan M.; Meyer, Michaël; Tucker, S. P.

doi:10.2514/6.2007-343

Cited by 17 publications

(7 citation statements)

References 7 publications

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“…8 An approximation used sucessfully in previous investigations utilizes TDK/VIPER to predict the pressure loss. 10 For the perfect injector approximation (TDK with boundary layer), the total pressure at the throat can be calculated using p o * F vac (1) where F vac is the measured thrust corrected for vacuum and the thrust coefficient, C F , is the perfect injector value assuming the pressure at the face of the injector as the chamber pressure. This method is most useful for small expansion ratios where the nozzle loss is small compared to the combustor inefficiency.…”

Section: A Fundamental Parametersmentioning

confidence: 99%

Vaporization and Zonal Mixing in Performance Modeling of Advanced LOX-Methane Rockets

Williams¹,

Stiegemeier²

2012

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

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Initial modeling of LOX-Methane reaction control (RCE) 100 lb f thrusters and larger, 5500 lb f thrusters with the TDK/VIPER code has shown good agreement with sea-level and altitude test data. However, the vaporization and zonal mixing upstream of the compressible flow stage of the models leveraged empirical trends to match the sea-level data. This was necessary in part because the codes are designed primarily to handle the compressible part of the flow (i.e. contraction through expansion) and in part because there was limited data on the thrusters themselves on which to base a rigorous model. A more rigorous model has been developed which includes detailed vaporization trends based on element type and geometry, radial variations in mixture ratio within each of the "zones" associated with elements and not just between zones of different element types, and, to the extent possible, updated kinetic rates. The Spray Combustion Analysis Program (SCAP) was leveraged to support assumptions in the vaporization trends. Data of both thrusters is revisited and the model maintains a good predictive capability while addressing some of the major limitations of the previous version. NomenclatureA* = Throat area, in 2 A e = Nozzle exit area, in 2 C* = Characteristic velocity, ft/s C F,PI = Thrust coefficient (for a perfect injector), lb f /lbm s F VAC = Thrust (adjusted to vacuum ambient conditions), lb f G = Mixture ratio variation factor I SP,VAC = Specific impulse (adjusted to vacuum ambient conditions), s L' = Characteristic length of the combustion chamber, in m = Mass flow rate, lb m /s MR = Mixture ratio, oxydizer to fuel ODE = Subscript indicating a value calculated assuming one-dimensional equilibrium flow p a = Ambient pressure, psia p e = Nozzle exit pressure, psia p o * = Effective chamber pressure, psia TDK = Two-dimensional kinetics code VIPER = Viscous Interaction Performance Evaluation Routine = Characteristic velocity efficiency = Specific impulse efficiency  MIX = Mixing efficiency 1 Senior Scientist, OAI, Propulsion and Propellants Branch, 21000 Brookpark Rd., MS 16-1, Associate Fellow. 2 Aerospace Engineer, Propulsion and Propellants Branch, 3000 Aerospace Parkway, AIAA Member.

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Section: A Fundamental Parametersmentioning

confidence: 99%

Vaporization and Zonal Mixing in Performance Modeling of Advanced LOX-Methane Rockets

Williams¹,

Stiegemeier²

2012

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

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“…Thermal management technology for a cryogenic propellant storage tank is an important component of future activity planning to achieve long-term space exploration [1][2][3] . The cryogenic propellant storage tank suffers loss of propellant due to boil-off, which is induced by heat leakage into the tank from the surrounding environment.…”

Section: Introductionmentioning

confidence: 99%

One-dimensional Droplet Model for Prediction of Jet-tip Height of Subcooling Mixing Jet for Cryogenic Propellant Storage Tank

Kawanami

Takeda

Matsushima

et al. 2021

Preprint

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This study proposes a one-dimensional droplet model to predict the jet-tip height of a subcooling mixing jet issuing from the bottom of a cryogenic propellant storage tank. Cryogenic liquids, such as liquid hydrogen and liquid oxygen, are used as propellants and oxidants in spacecraft propulsion systems that require long-term storage in a closed tank. However, thermal stratification forms near the gas-liquid interface during long-term storage of cryogens due to heat flowing into the tank from the surrounding environment. In addition, boil-off gas (BOG) is generated from the interface, which causes increased pressure in the tank. To reduce the BOG, it is effective to destroy the thermal stratification by mixing in the cold jet issuing from the bottom of the tank. Ground experiments using FC-72 and water as test fluids are conducted to investigate the behavior of the jet using the proposed one-dimensional spherical droplet model as the tip of the jet. The jet behavior is visualized using the Shadowgraph system and the height of the jet-tip is investigated under various experimental conditions. The proposed model is also verified by comparison with experimental data available in the literature. The results show that the proposed model aligns well with the experimental data.

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“…Although PCAD encompasses all green cryogenic propellants including liquid hydrogen for 2006 the project was focused on developing technologies in liquid oxygen and liquid methane as technologies for these propellants are less mature (ref. 22). …”

Section: E Propulsion and Cryogenic Advanced Developmentmentioning

confidence: 99%

Cryogenic Technology Development for Exploration Missions

Chato

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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Cryogenic Fluid Management Technologies for Advanced Green Propulsion Systems

Cited by 17 publications

References 7 publications

Vaporization and Zonal Mixing in Performance Modeling of Advanced LOX-Methane Rockets

Vaporization and Zonal Mixing in Performance Modeling of Advanced LOX-Methane Rockets

One-dimensional Droplet Model for Prediction of Jet-tip Height of Subcooling Mixing Jet for Cryogenic Propellant Storage Tank

Cryogenic Technology Development for Exploration Missions

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