Three-duct ACE engine with Flade fan and core machine driving fan

Abstract

The invention provides a three-duct ACE engine with a Flade fan and a core machine driving fan. Compared with a conventional small-duct-ratio turbofan engine, the three-duct ACE engine is structurally characterized in that the fan is divided into a front fan and a rear fan, the front fan with Flade is located on a low-pressure rotor, and the rear fan, namely the core machine driving fan, is located on a high-pressure rotor. The front fan and the rear fan are each provided with an outlet duct, so that the duct ratios in different flight states are adjusted within a wide flight envelope range, and the air flow of each duct is better controlled. The rear fan, namely the core machine driving fan, is arranged through a high-pressure turbine driving structure, the acting capacity of a high-pressure turbine can be fully utilized, the situation that the rear fan is driven by a low-pressure turbine, and consequently the number of stages of the low-pressure turbine is increased is avoided, the quality of the engine is improved, and the thrust-weight ratio is reduced.

Description

technical field [0001] The invention relates to the field of aircraft power design, relates to a supersonic aircraft power system with a wide envelope of use, and in particular to a three-duct adaptive cycle engine (ACE, Adaptive Cycle Engine) layout with a Flade fan and a core machine driving fan stage . Background technique [0002] After more than half a century of development, the unit fuel consumption rate and thrust-to-weight ratio of military aeroengines have been continuously improved, greatly improving the mission capabilities of military aircraft. With the further development of electronic technology and the further improvement of missile functions, major changes have taken place in combat methods, which put forward higher requirements for the performance of military aircraft, such as beyond-visual-range combat, supersonic penetration, close-range combat, post-stall maneuvering, and short-range combat. Or vertical take-off and landing, larger flight envelope and c...

AI Technical Summary

Problems solved by technology

In the past 40 years, major aero-engine companies, universities and research institutions at home and abroad have carried out related research on variable-cycle engines with different layouts, including selection of venting variable-cycle layouts, dual-compression system variable-cycle layouts , double external culvert variable cycle layout with CDFS, turbo / ram variable cycle combined layout (J58 engine based on this layout has been finalized and applied to SR-71 reconnaissance aircraft), but the above layout has not yet formed the largest variable cycle, high-altitude subsonic The fuel consumption rate is still high, and the range of the bypass ratio of the engine should be larger

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