Afterburning small turbofan engine for supersonic missile

Abstract

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).

Description

Technical field [0001] This patent relates to a turbo propulsion device, in particular to an afterburner small turbofan engine for supersonic missiles. Background technique [0002] Subsonic cruise, supersonic penetration and terminal attack are the development direction of advanced stealth cruise missiles in the future. In order to achieve this goal, it is first necessary to solve the problem of missile propulsion. Turbofan engines have higher propulsion efficiency and lower infrared radiation characteristics. Advanced cruise missiles all over the world use small turbofan engines as their power devices, but the existing small turbofan engines have relatively small thrust-to-weight ratios. There is no afterburner designed, and its maximum available thrust is not enough to meet the needs of missile supersonic flight. The SR-71 Blackbird reconnaissance aircraft uses a turbojet and ram-combustion combined engine structure as its propulsion device. At low speeds, the turbojet engine...

AI Technical Summary

Problems solved by technology

Since the SR-71 Blackbird reconnaissance aircraft needs long-term high-altitude supersonic cruise, the engine needs to work in the ram state for a long time, and it needs to cooperate with complex inlet and nozzle adjustment devices to ensure high propulsion efficiency and stable working characteristics. Therefore, This type of power plant is difficult to miniaturize and transplant to cruise missiles

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