Abstract
This study starts from the design theory of the holes on the combustion chamber liners . I designed the combustion chamber to reach the standards of KingTech K170-F micro-turbojet engines. The designed chamber was then assembled onto the K170-F turbo-engine in order to test the performance and analyze the combustion in the chamber. This study had three stages: (1) The performance of the K170-F turbo-engine was measured, and the turbine analysis program was used to calculate the conditions inside the turbo-engine, which in later stages would be referred to as the basics and restrictions; (2) Those conditions measured in last stage and the related theories were used to design a combustion chamber, in which details were all covered, including the geometrical chamber size, the positions and the diameters of the chamber liner holes, and the air flow rates of all combustion areas; (3) The chamber was assembled onto the K170-F turbo-engine, the performance of the running turbo-engine was measured, and then the testing results of the turbo-engine was compared with the designed chamber with the original ones in order to further analyze the combustion inside the chamber. The experimental results show that the chamber I designed can be applied to real turbo-engines and that the performing difference between the designed chamber and the original one is not significant. This study serves as a successful attempt to design a combustion chamber for a micro turbo-engine.