Sharif Digital Repository

The propulsion system plays a significant role in determining of mission and flight regime of an air craft. This system, provides the propulsion force for an air craft. A comprehensive model based on the specifications of gas turbine cycle, with acceptable accuracy, is necessary for quick estimating of the engine performance in different phases of design and development of a propulsion system. The structure and performance of the turbojet engine is elaborated in this project and the previous researches and their simulating methods of the turbojet engine are reviewed. The research plan is justified by explanation of the project’s objects and its assumptions. Then, the zero-dimensional... 

This research is done as a continuation of previous efforts to develop a turbojet engine from a turbocharger at departments of mechanical and aerospace engineering of Sharif University of Technology and describes the necessary steps in order to design and build a dual fuel combustion chamber for a small, turbocharger based turbojet engine. At first, zero-dimensional analysis is done using a code written in Matlab. Using this code, matching of the compressor and turbine in the turbojet thermodynamic cycle is verified and the operating line of the turbojet engine has been extracted. Henceforth, operating conditions of the combustion chamber to start design process is determined. In designing...