The invention relates to an aero-engine fuel system. The aero-engine fuel system comprises a fuel tank, a low-pressure pump, a high-pressure gear pump, an opening valve, a two-stage filtering device, a fuel regulating valve, an isobaric regulating valve and a main fuel path, wherein the fuel tank is used for storing fuel, the low-pressure pump is connected with the outlet end of the fuel tank through a fuel supply pipeline, the high-pressure gear pump is connected with the outlet end of the low-pressure pump through the fuel supply pipeline, the opening valve is connected with the outlet end of the high-pressure gear pump through the fuel supply pipeline, a first-stage filtering device of the two-stage filtering device is mounted at the front section of the inlet end of the high-pressure gear pump, a second-stage filtering device of the two-stage filtering device is mounted at the front section of the inlet end of the opening valve, the fuel regulating valve is connected with the outlet end of the opening valve through the fuel supply pipeline, the inlet end of the isobaric regulating valve is communicated with the part, between the second-stage filtering device and the inlet end of the opening valve, of the fuel supply pipeline and is used for regulating and controlling the inlet pressure of the opening valve, the outlet end of the isobaric regulating valve is communicated with the part, between the outlet end of the opening valve and the fuel regulating valve, of the fuel supply pipeline and is used for regulating and controlling the outlet pressure of the opening valve, and the main fuel path is connected with the outlet end of the fuel regulating valve through the fuel supply pipeline. The aero-engine fuel system has the characteristics of simple structure, reliable fuel supply power, small dead weight and the like.