Micro gas turbine (MGT) has the characteristics of small size, light weight, strong fuel adaptability, high power generation efficiency and low pollution. As a relatively mature distributed power source, they have attracted wide attention. Combustor is an important component of micro gas turbine, and its structure has an important impact on the performance of gas turbine. In this study, a combustor suitable for micro gas turbine is designed and analyzed by numerical simulation. The combustor adopts the reverse flow structure, swirler structure and centrifugal nozzle fuel supply mode, which can well organize the flow and combustion, and can form a stable swirl area at the head of the combustion liner. The combustion efficiency can reach 99%, and the total pressure loss is 2%.
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Yang et al. (2024) studied this question.
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