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Flow Analysis of Space Shuttle Feed Line 17-inch Disconnect ValveA steady incompressible three-dimensional viscous flow analysis has been conducted for the Space Shuttle External Tank/Orbiter propellant feed line disconnect flapper valves with upstream elbows. The full Navier-Stokes code, INS3D, is modified to handle interior obstacles. Grids are generated by SVTGD3D code. Two dimensional initial grids in the flow cross section with and without the flappers are improved by elliptic smoothing to provide better orthogonality, clustering and smoothness to the three dimensional grid. The flow solver is tested for stability and convergence in the presence of interior flappers. An under-relaxation scheme has been incorporated to improve the solution stability. Important flow characteristics such as secondary flows, recirculation, vortex and wake regions, and separated flows are observed. Computed values for forces, moments, and pressure drop are in satisfactory agreement with water flow test data covering a maximum tube Reynolds number of 3.5 x 10(exp 6). The results will serve as a guide to improved design and enhanced testing of the disconnect.
Document ID
19880061622
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
External Source(s)
Authors
Kandula, Max
(Lockheed Engineering and Management Services Co., Inc. Houston, TX, United States)
Pearce, Daniel
(Lockheed Engineering and Management Services Co., Inc. Houston, TX, United States)
Date Acquired
August 13, 2013
Publication Date
July 25, 1988
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA PAPER 88-3788
Meeting Information
Meeting: AIAA/ASME/SIAM/APS National Fluid Dynamics Congress
Location: Cincinnati, OH
Country: United States
Start Date: July 25, 1988
End Date: July 28, 1988
Accession Number
88A48849
Funding Number(s)
CONTRACT_GRANT: NAS9-17900
Distribution Limits
Public
Copyright
Public Use Permitted.
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