Design of Thermodynamic Vent/Screen Baffle Cryogenic Storage System

Cady, E. C.

doi:10.2514/3.57008

Cited by 23 publications

(12 citation statements)

References 2 publications

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“…Review of the video should improve the accuracy of reseal times. Comparison of our results to those reported in Cady 14 show very similar values.…”

Section: Resultssupporting

confidence: 77%

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Screen Channel Liquid Acquisition Devices for Cryogenic Propellants

Chato¹,

Kudlac²

2002

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Review of the video should improve the accuracy of reseal times. Comparison of our results to those reported in Cady 14 show very similar values.…”

Section: Resultssupporting

confidence: 77%

“…Burge and Blackmon 13 study screen channel designs to support shuttle auxiliary propulsion and a space tug like vehicle. Cady 14 expands on the work of Burge and Blackmon to include fuel reactant storage. He also includes some of the first data on the bubble point of fine mesh Dutch twill screens in liquid hydrogen.…”

Section: Shuttle Eramentioning

confidence: 99%

Screen Channel Liquid Acquisition Devices for Cryogenic Propellants

Chato¹,

Kudlac²

2002

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Results are in fair agreement with Cady's [25] previously reported non-inverted bubble point (NIBP) results using a 325x2300 mesh and GHe; he showed a smaller degradation factor (despite higher heat transfer rates) of only 10% at a gas temperature 55K above the liquid temperature. However, Cady also reported near identical degradation in performance for several different meshes, which is in disagreement with the current study.…”

Section: Screen Screen Thicknesssupporting

confidence: 92%

“…Cady [25] reported NIBP test data for a standard 325x2300 screen, a pleated 325x2300, a stainless steel (SS) and aluminum (Al) 200x1400 screen, a 720x140, 165x800, and a SS and Al 120x120 screen in LH 2 using warm GHe. There is degradation in heated bubble point values for all meshes tested, with the largest red uction in performance for the 200x1400 screen.…”

Section: Discussionmentioning

confidence: 99%

Warm Pressurant Gas Effects on the Static Bubble Point Pressure for Cryogenic LADs

Hartwig

McQuillen²,

Chato³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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This paper presents experimental results for the liquid hydrogen and nitrogen bubble point tests using warm pressurant gases conducted at the NASA Glenn Research Center. The purpose of the test series was to determine the effect of elevating the temperature of the pressurant gas on the performance of a liquid acquisition device (LAD). Three fine mesh screen samples (325x2300, 450x2750, 510x3600) were tested in liquid hydrogen and liquid nitrogen using cold and warm non-condensable (gaseous helium) and condensable (gaseous hydrogen or nitrogen) pressurization schemes. Gases were conditioned from 0K -90K above the liquid temperature. Results clearly indicate degradation in bubble point pressure using warm gas, with a greater reduction in performance using condensable over non-condensable pressurization. Degradation in the bubble point pressure is inversely proportional to screen porosity, as the coarsest mesh demonstrated the highest degradation. Results here have implication on both pressurization and LAD system design for all future cryogenic propulsion systems. A detailed review of historical heated gas tests is also presented for comparison to current results. Nomenclatured shute = Diameter of the shute wire [μm] d warp = Diameter of the wap wire [μm] D p = Effective pore diameter [μm] g = Gravitational acceleration [m/s 2 ] HEX = Heat exchanger LL = Liquid Level above LAD screen [m] l s = Distance between consecutive shute wires [μm] n shute = Number of shute wires per inch of screen [1/m] n warp = Number of warp wires per inch of screen [1/m] PCA = Pressure control assembly t = Screen thickness [μm] ΔP BP = Bubble point pressure [Pa] ΔT = Temperature difference between liquid and pressurant gas [K] ε = Porosity γ = Surface tension [mN/m] ρ LH2 = Liquid hydrogen density [kg/m 3 ] θ c = Contact angle [degrees]

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“…As was mentioned earlier, screen channel LADs have proven flight heritage with storable propellants, but, only ground testing has been conducted for cryogenic LOX and LH 2 using these fine mesh screens. Previously reported bubble points for the most popular 325×2300 mesh screen are plotted in Figure 3, which includes data for LH 2 , liquid nitrogen (LN 2 ), LOX, liquid methane (LCH 4 ) and IPA from Paynter (1973), , Cady (1973Cady ( , 1975Cady ( , 1977, Chato and Kudlac (2002), Kudlac and Jurns (2006), and Jurns et al (2007), respectively. The black line is the predicted values using Equation (2) and a pore diameter specified from Hartwig and Mann (2013a).…”

Section: Performance Gainsmentioning

confidence: 99%