Analysis of regenerative cooling ın liquid propellant rocket engines

Download
index.pdf
2008
Boysan, Mustafa Emre
Show full item record
1461
views
534
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, 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 and changing the cross sectional area in non-critical regions for heat flux, the rocket combustion chamber gas side wall temperature can be reduced significantly without an increase in the coolant pressure drop. 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/Kerosene mixture at a chamber pressure of 60 bar with 300 kN thrust and kerosene is considered as the coolant. A numerical investigation was performed to determine the effect of different aspect ratio cooling channels and different number of cooling channels on gas-side wall and coolant temperature and pressure drop in cooling channel.
Mechanical engineering.
http://etd.lib.metu.edu.tr/upload/12610190/index.pdf
https://hdl.handle.net/11511/18308
Graduate School of Natural and Applied Sciences, Thesis

Suggestions

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...
Validation of MISES Two-Dimensional Boundary Layer Code for High-Pressure Turbine Aerodynamic Design
ANDREW, PHILIP; Kahveci, Harika Senem (ASME International, 2009-07-01)
Avoiding aerodynamic separation and excessive shock losses in gas turbine turbomachinery components can reduce fuel usage and thus reduce operating cost. In order to achieve this, blading designs should be made robust to a wide range of operating conditions. Consequently, a design tool is needed-one that can be executed quickly for each of many operating conditions and on each of several design sections, which will accurately capture loss, turning, and loading. This paper presents the validation of a bounda...
Comparison of different aspect ratio cooling channel designs for a liquid propellant rocket engine
Boysan, M. E.; Ulaş, Abdullah; Toker, K. A.; Seckin, B. (2007-06-16)
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, ...
Computer aided engineering of an unmanned underwater vehicle
Cevheri, Necmettin; Aksel, Mehmet Haluk; Department of Mechanical Engineering (2009)
Hydrodynamic and thermal analyses performed during the conceptual design of an unmanned underwater vehicle are presented in this study. The hull shape is determined by considering alternative shapes and the dimensions are determined from the internal arrangement of components. Preliminary thermal analyses of the watertight section are performed with a commercial software called FLUENT to check the risk of over-heating due to the heat dissipation of devices. Performance of the proposed hull design is analyze...
Performance anallysis of an intermediate temperature solid oxide fuel cell
Timurkutluk, Bora; Tarı, İlker; Department of Mechanical Engineering (2007)
An intermediate temperature solid oxide fuel cell (SOFC) is developed and its performance is investigated experimentally and theoretically. In the experimental program, a gadolinium doped ceria based membrane electrode group is developed with the tape casting and screen printing methodology and characterized. An experimental setup is devised for the performance measurement of SOFCs and the performance of produced cells is investigated over a range of parameters including the electrolyte thickness, the sinte...
Citation Formats
M. E. Boysan, “Analysis of regenerative cooling ın liquid propellant rocket engines,” M.S. - Master of Science, Middle East Technical University, 2008.
METU IIS - Integrated Information Service open@metu.edu.tr