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Design and Manufacturing of a Miniature Turbojet Engine

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Design and Manufacturing of a Miniature Turbojet Engine ( design-and-manufacturing-miniature-turbojet-engine )

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DESIGN OF MINIATURE TURBOJET ENGINE 23 allowable tensile strength of the material used. It should be noted that the center of the turbine wheel experiences centrifugal forces up to three times as high as the blades due to a stress concentration at the hole (Kamps, 2005). Common turbine wheel designs account for this by employing a thicker center of the disk than along the outsides. 2.2.D. Combustion Chamber The purpose of the combustion chamber is to retrieve air from the compressor stage and deliver it at much greater temperatures to the turbine stage, this is where heat is added to the cycle by burning fuel. The diffuser section of the compressor stage decelerates the airflow in order to increase pressure before it reaches the combustion chamber. This high-pressure air stores potential (pressure) energy and will produce better combustion and cycle efficiency. Energy is further increased through combustion of injected fuel, usually kerosene, and the high-pressure air (Hunecke, 1997). Average air/fuel ratios range from around 45:1 to 130:1 for the entire combustion chamber however fuel will only burn efficiently around the stoichiometric air/fuel ratio, 15:1. As this project is concerned with combustion chamber design, it should be noted that many advancements in combustion chamber design have been founded upon empirical data and experimentation (NASA, 1973). Therefore, design of combustion chambers relies heavily on the analysis of previous, similarly designed systems. Two common types of combustion chambers have been developed, the cylindrical, or can chamber, and the annular chamber. A single annular chamber can be employed quite effectively in a turbojet engine while being conducive to minimizing weight, cost,

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