NDLI: Comparison of Different Aspect Ratio Cooling Channel Designs for a Liquid Propellant Rocket Engine

Content Provider	IEEE Xplore Digital Library
Author	Boysan, M.E. Ulas, A. Toker, K.A. Sedan, B.
Copyright Year	2007
Description	Author affiliation: Roketsan Missile Ind. Inc., Ankara (Boysan, M.E.)
Abstract	High combustion temperatures and long operation durations require the use of cooling techniques in liquid propellant rocket engines. For high-pressure and high-thrust rocket engines with long operation times, regenerative cooling is the most preferred cooling method. In regenerative cooling, a coolant flows through passages formed either by constructing the chamber liner from tubes or by milling channels in a solid liner. Traditionally, approximately square cross sectional channels have been used. However, recent studies have shown that by increasing the coolant channel height-to-width aspect ratio, the rocket combustion chamber hot-gas-side wall temperature can be reduced significantly. In this study, the regenerative cooling of a liquid propellant rocket engine has been numerically simulated. The engine has been modeled to operate on a $LOX/GH_{2}$ mixture at a chamber pressure of 68 atm and $LH_{2}$ (liquid-hydrogen) is considered as the coolant. A numerical investigation was performed to determine the effect of different aspect ratio cooling channels and different coolant mass flow rates on hot-gas-side wall temperature and coolant pressure drop. The variables considered in the cooling channel design were the number of cooling channels and the cooling channel cross-sectional geometry along the length of the combustion chamber.
Starting Page	225
Ending Page	230
File Size	4825603
Page Count	6
File Format	PDF
ISBN	1424410568
DOI	10.1109/RAST.2007.4283982
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2007-06-14
Publisher Place	Turkey
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Geometry Rockets Temperature Cooling Milling Propulsion Coolants Numerical simulation Combustion Engines
Content Type	Text
Resource Type	Article

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