Numerical Investigation of a Novel Mechanism for Cooling Raptor Engine Bell Nozzle
Supervisor Name
Luqman Herzallah
Supervisor Email
luqman.h@najah.edu
University
An-Najah National University
Research field
Mechanical Engineering
Bio
Eng. Luqman Herzallah is an instructor at An-Najah National University in the mechanical engineering department. He delivered lectures for different courses such as Dynamics, Vibrations, Turbomachinery, MATLAB programming … etc. He is the coordinator of laboratories committee, and he is a member of automotive program committee, where he participated strongly in designing course map for the program, and in the formation of new automotive laboratories for both traditional and new vehicles including hybrid and electric ones. Eng. Herzallah published different scientific papers in a respected journals, he was awarded twice by the “Award of the Regulations of Awards for Research Excellence and Publication Quality”. He earned his MSc. degree from Poleticnico di Torino, Italy, where he was awarded by the ERASMUS MUNDUS scholarship.
With the rapid technological development in the field of space exploration, it has become important to research and delve deeper into the propellant nozzles of rocket engines. As long as these engines have been the way that the researchers used to reach and explore the space. The engines emit a core flow at very high temperatures, which comes into contact with the inner wall of the nozzle, and the temperature increases more and more until it approaches the sonic region, known as the nozzle throat. This makes the study and research of cooling systems for nozzles a critical matter. Cooling systems act to preserve the geometry of the engine which is required for its functioning. Such solutions were necessitated when the need arose to ensure thermal protection for the materials that made up the engine nozzles. For example, parts to which significant heat is applied during operating period can be cooled by regenerative fuel. This study proposes an innovative solution in the propellant nozzle cooling system, where a novel geometry will be designed and sketched using SOLIDWORKS software, and then it will be processed by CFD ANSYS software to simulate the nozzle cooling process and clarify the effect of high temperatures, which leads to deformation of the material from which the combustion engine nozzle is made, which affects the efficiency of the engine and also the efficiency of combustion, and causes poor engine performance. This study is very important to aerospace engineering, it serves new solutions for an old problem. The type of this study is still a hot topic, but the geometry that will be adopted in this study is new geometry and never been studied for this application before, and it is expected to have a great influence on the efficiency of rocket nozzle cooling process.
