To achieve zero carbon emissions from aviation engines,hydrogen fuel was used to modify the design,and simulation analysis of a certain type of fuel engine combustor was carried out.In order not to affect the requirements of the turbine for the temperature field at the outlet of the combustor,the hydrogen conversion design of the combustor was based on the principle of similar temperature fields and unchanged air flow distribution in the flame tube.At the same time,based on the principle of minimizing modification design,only the dome(including the nozzle)was newly designed,and the casing was adaptively modified.Through numerical simulation analysis,it has been found that the flow field of the hydrogen conversion scheme is different from that of the fuel scheme,with the presence of angular recirculation zone and main recirculation zone,and the high temperature zone concentrated in the main recirculation zone and shear layer.Compared with the temperature field of the fuel scheme,it has been found that the radial temperature distribution curve of the outlet is around 2/3 of the blade height,and the outlet temperature field is more uniform.The outlet temperature distribution factor is around 0.154 with higher combustion efficiency,indicating that the improved design has little impact on the turbine.
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