Sharif Digital Repository

In the present study, design and manufacturing of a connected pipe liquid fuel ramjet test platform is implemented for performance investigation of a research liquid fuel ramjet burner in the thermodynamic flight conditions. Design and manufacturing of platform systems include: the hot air supply system, the liquid fuel system and the square cross-sectional combustion chamber with the v-gutter shape flame holder. In order to determine the performance range of subsystems, calibration process has been carried out. Calibration process of the hot air supply system includes: determining of the burner inlet velocity and temperature. Also, calibration of the liquid fuel system includes: determining... 

In this thesis a combustion chamber of a liquid-fueled ramjet missile will be simulated. At first a history of construction and designing of ramjet missiles will be expressed then studies in the filled of simulation and optimization of combustion chamber will be expressed. In this simulation for modeling of spray increasing accuracy we used Lagrangian method. All simulations are done in the fluent software. For validation, we simulated the experimental model that was examined by Sasaki et. Al. and observed that our result are almost matched with their experimental data. Finally for simulation we selected the ramjet engine of Markudet Company. Selected fuel is liquid n-Heptan. One of the... 

In the present study an air supply system of a connected-pipe ramjet test facility for liquid fuel ramjet engine in theoretical and numerical base designed and optimized that the purpose is for performance test of a ramjet engine combustor in flight condition. The flight condition gained from previous assessment that is 1.5 kg air in 10 bars and 550 K. Air supply subsystems consist of air tanks, compressors, valves, regulators, preheater, and fuel and oxygen systems that are designed in a preliminary process and then valves, orifices, and fuel and oxygen systems optimized by HYSYS program. In the last step preheater that is a gas turbine combustor investigated and possible changes made by... 

Heat transfer to combustion chamber walls is an unwanted phenomenon. Reduction of this heat transfer by using bidirectional swirl flow, as proved in past studies, can result in time and cost saving methods in design and fabrication of combustion chambers. Bidirectional Swirl flow, existing in vortex engine, maintains the chamber wall cool. This characteristic of such flow field, among with many other advantages for it, makes researchers more interested in studying the propulsion of it as well as its other applications. Bidirectional swirl flow in liquid fuel ramjet engines has the proven advantage of keeping the combustion chamber walls cool and in solid fuel ramjet engines in increasing the... 

During the last 5 decades, the operation of scramjet engines has not been without limitations and technical challenges; i.e., the start-up speed of the engine. Conventional scramjet engines do not have the ability to start from a standstill and even at a flight Mach lower than 5. Therefore, reducing the start-up speed of the scramjet engine is not only very attractive in terms of operation but it will also reduce many technical challenges. The purpose of this research is to identify and analyze the flight speed to start the scramjet engine and the requirements to achieve it. In this regard, first by examining the quasi-one-dimensional equations of gas dynamics, the effect of the static...