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Title: |
Analysis of Regen Cooling in Rocket Combustors
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Author(s): |
Merkle, C. L.; Li, D.; Sankaran, V.
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Abstract: |
The use of detailed CFD modeling for the description of cooling in rocket chambers is discussed. The overall analysis includes a complete three-dimensional analysis of the flow in the regenerative cooling passages, conjugate heat transfer in the combustor walls, and the effects of film cooling on the inside chamber. The results in the present paper omit the effects of film cooling and include only regen cooling and the companion conjugate heat transfer. The hot combustion gases are replaced by a constant temperature wall boundary condition. Load balancing for parallel cluster computations is ensured by using single-block unstructured grids for both fluids and solids, and by using a 'multiple physical zones' to account for differences in the number of equations. Validation of the method is achieved by comparing simple two-dimensional solutions with analytical results. Representative results for cooling passages are presents showing the effects of heat conduction in the copper walls with tube aspect ratios of 1.5:l.
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NASA Center: |
Marshall Space Flight Center
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Publication Date: |
May 13, 2004
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Document Source: |
CASI |
Online Source: |
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Document ID: |
20040075891
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Publication Information: |
Number of Pages = 8 |
Contract-Grant-Task Number: |
NCC8-200 |
Price Code: |
A02 |
Meeting Information: |
52nd JANNAF Joint Propulsion Meeting, 10-14 May 2004, Las Vegas, NV, United States |
Keywords: |
COMBUSTION CHAMBERS; THREE DIMENSIONAL MODELS; REGENERATIVE COOLING; HEAT TRANSFER; FILM COOLING; TWO DIMENSIONAL MODELS; COMPUTATIONAL FLUID DYNAMICS; COPPER;
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Accessibility: |
Unclassified; No Copyright; Unlimited; Publicly available; |
Updated/Added to NTRS: |
2008-06-02 |
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