Comparison of different aspect ratio cooling channel designs for a liquid propellant rocket engine

Date

2007-06-16

Author

Boysan, M. E.
Ulaş, Abdullah
Toker, K. A.
Seckin, B.

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

54
views

0
downloads

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 LH2 (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.

Subject Keywords

Aerospace, Remote sensing, Engineering, Mechanical, LOX/GH(2) mixture, LH2 (liquid-hydrogen)

URI

https://hdl.handle.net/11511/38178

DOI

https://doi.org/10.1109/rast.2007.4283982

Collections

Department of Mechanical Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Analysis of regenerative cooling ın liquid propellant rocket engines Boysan, Mustafa Emre; Ulaş, Abdullah; Department of Mechanical Engineering (2008) 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, 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 ...
Numerical analysis of regenerative cooling in liquid propellant rocket engines Ulaş, Abdullah (2013-01-01) High combustion temperatures and long operation durations require the use of cooling techniques in liquid propellant rocket engines (LPRE). For high-pressure and high-thrust rocket engines, regenerative cooling is the most preferred cooling method. Traditionally, approximately square cross sectional cooling channels have been used. However, recent studies have shown that by increasing the coolant channel height-to-width aspect ratio and changing the cross sectional area in non-critical regions for heat flux...
Experimental investigation of near and far field flow characteristics of circular and non-circular turbulent jets Taşar, Gürsu; Özgen, Serkan; Department of Aerospace Engineering (2008) The atomization problem of high speed viscous jets has many applications in industrial processes and machines. In all these applications, it is required that the droplets have high surface area/volume ratio meaning that the droplets should be as small as possible. This can be achieved with high rates of turbulence and mixing of the flow. In order to constitute a foresight of geometry e ects on droplet size, experimental investigation and the determination of flow characteristics in near and far fields of a ...
Experimental study of solid propellant combustion instability Çekiç, Ayça; Ulaş, Abdullah; Department of Mechanical Engineering (2005) In this study, experimental investigation of solid propellant combustion instability using an end burning T-Burner setup is performed. For this purpose, a T-Burner setup is designed, analyzed, constructed and tested with all its sub components. T-Burner setup constructed is mainly composed of a base part, a control panel and the T-Burner itself. Combustion chamber, pressure stabilization mechanism, pressurization system, measurement instruments and data acquisition systems form the T-Burner. Pressure stabil...
Passive flow control in liquid-propellant rocket engines with cavitating venturi Ulaş, Abdullah (Elsevier BV, 2006-04-01) In a companion liquid rocket engine development project, due to the overall weight constraint of the propulsion system, a cavitating venturi is selected to control the liquid fuel and liquid oxidizer mass flow rates. Two cavitating venturis, one for the fuel and the other for the oxidizer, are designed to deliver the desired mass flow rates for a specified operating inlet pressure, temperature, and inlet cross-sectional area. The converging and diverging angles of the venturis are selected from the literatu...

Citation Formats

M. E. Boysan, A. Ulaş, K. A. Toker, and B. Seckin, “Comparison of different aspect ratio cooling channel designs for a liquid propellant rocket engine,” 2007, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/38178.