## 1 Introduction  
The term'micro gas turbine' is typically used to describe small gas turbines with a thrust level of 1000 N or less. These engines are employed as a propulsion system for unmanned aerial vehicles (UAVs) and small airplanes in a variety of fields, including civilian and military applications, primarily due to their compact size, low cost, straightforward structure, and minimal maintenance requirements. In the early days of micro gas turbine development, these engines were primarily utilized for civilian applications, such as hobby RC airplanes or research aircraft. However, in recent years, micro gas turbine engines have become an increasingly significant area of military interest. As the use of micro gas turbine engines continues to expand, research in a range of fields has been undertaken. Most of the research in this field is dedicated to the analysis and prediction of gas turbine performance, with a particular emphasis on engine and component optimization to enhance efficiency. This research area is still under active investigation. In the domain of analytical research, a case study was conducted by [PERSON] et al. [1] to implement a one-dimensional thermodynamic analysis model of an entire engine. Verification of the analysis model with the test results revealed a high degree of similarity, even at off-design points. [PERSON] et al. [2] developed an analytical model that incorporates the secondary flow path of the engine using the MATLAB SIMULINK. In a related study, [PERSON] et al. [3] implemented a performance analysis program for a gas turbine with a thermodynamic model using MATLAB. In addition to thermodynamic modeling studies, various component-level 3D analysis studies have also been conducted. For example, [PERSON] [4] analyzed and optimized the performance of centrifugal compressors in micro gas turbine engines. Similarly, [PERSON] [5] studied the design process of small centrifugal compressors and the performance prediction of compressors. [PERSON] et al. [6; 7] employed computational analysis to characterize the aerodynamic performance of centrifugal compressors for micro gas turbines and to identify the causes of compressor losses at high RPM. They also proposed a method for improving flow matching by flow cuts to reduce losses. In the context of combustor research, [PERSON] et al. [8; 9] conducted a study to design and fabricate an ultra-compact combustor (UCC) for micro gas turbines. This involved reducing the size of the combustor by one-third. [PERSON] et al. [10] conducted a combustor design study to improve the combustion efficiency of micro gas turbines. The combustion efficiency was evaluated by fabricating the designed combustor via additive manufacturing (AM) and conducting combustion tests. [PERSON] [11] created a model of the combustor of an actual micro gas turbine to analyze the internal combustion reaction. Other studies related to the exhaust nozzle include an analysis of exhaust nozzle geometry and an observation of infrared signal characteristics by [PERSON] et al. [12]. As in the preceding studies presented above, various analysis model implementation studies have been conducted for prediction and optimization studies, conducted in two ways: thermodynamic model and 3D CFD. In the case of the thermodynamic model, the performance of each component is predicted by finding the point at which the performance for each element is matched. This approach offers the advantage of reduced analysis time; however, it necessitates the utilization of a performance map for each component. Also, it is not possible to observe the detailed thermo-fluid characteristics inside the engine. In contrast, component-level 3D CFD has the advantage of being able to observe the detailed thermo-fluid characteristics through the internal flow field, and relatively accurate performance prediction of components is possible. However, it is impossible to make a similar prediction at the system level.