The invention relates to a boosting type small turbofan engine for a supersonic missile. The boosting type small turbofan engine is characterized by comprising an engine body (1), an engine inlet (10), an engine outlet (17), a boosting combustor (18), a boosting combustor fuel spray nozzle (13), a primary low pressure fan (2), a low pressure rotating shaft (3), a boosting turbine (12), a secondaryhigh pressure fan (4), a high pressure rotating shaft (9), a high pressure gas compressor (6), and a high pressure turbine (11); the primary low pressure fan (2) and the boosting turbine (12) are installed at both ends of the low pressure rotating shaft (3); the secondary high pressure fan (4) and the high pressure gas compressor (6) are installed at one end of the high pressure rotating shaft (9), and the high pressure turbine (11) is installed at the second end of the high pressure rotating shaft (9); the low pressure rotating shaft (3) is sleeved with the high pressure rotating shaft (9);the boosting combustor fuel spray nozzle (13) and the boosting turbine (12) are both located in the boosting combustor (18), and the boosting turbine (12) directly faces the boosting combustor fuel spray nozzle (13).