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4 Discussion 4.1 Engine type Some different variations of the design were considered. After looking at other model sized jet engines we tried to make on with a simple shape and few, simply machined parts. For practical reasons a centrifugal compressor was chosen, since we could then achieve greater compression with a single stage. To save time we chose an already made compressor from a turbo instead of trying to build one ourselves. For the turbine the axial type is more easily realized since only one stage would be needed. 4.2 Materials When selecting the materials, the operating temperature had to be taken into consider- ation. Since the use of jet fuel was out of the question, due to safety, the simplest and most accessible solution was propane. To be able to operate at a high temperature ma- terial chosen for the majority of the engine was steel. Steel has a melting point at about 1500 ◦C, and propane burns at 1900 ◦C, but since a greater part of the air bypasses the combustion the operating temperature is much lower, and can be varied with the supply of fuel. The housing, the combustion chamber and the shaft was all made from steel, which gave a solid and stable foundation. The compressor plate, the inlet, and the turbine plate was made from aluminium. Which is a more manageable material that allowed more details in the construction work. Problems with high temperature could only affect the turbine plate, since it is located directly after the combustion chamber. Therefore a protective coating, made of steel, had to be manufactured and placed on top of the plate. The fuel line was made of a copper tube, which is good for avoiding corrosion. Due to its flexibility, the tube could be easily formed to a circle and placed on the front of the combustion chamber. Brass pieces were silver soldered to the tube to provide an inlet for the fuel into the chamber. 4.3 Compressor The chosen compressor was a radial compressor, taken from a turbocharger used in an automotive engine. This was seen as the easiest way to get a compressor without building one. But after further work and study on the subject it became clear that the compressor used was insufficient for the design made. As can be seen in fig 30 the compressor’s intended range of operation is at very high speeds, and even then the pressure ratio is not particularly high, there is not even any data for the speeds we could hope to achieve. We made the conclusion that this turbo was made with high efficiency rather than high pressures in mind. The compressor had backwards curved vanes, which gives a lesser flow rate than one of radial vanes but instead it has a higher efficiency. The assumption that it would be too hard to make a compressor, may have been wrong. After being in the workshop, and later noticing the insufficient compressor, the idea of making a compressor did not seem so distant anymore. It would be possible to make a 27PDF Image | Design and construction of a simple turbojet engine
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