Aeronautical propulsion system

Abstract

The invention provides an aeronautical propulsion system including a main engine (1), shafts, transmissions and a ducted fan. The shafts are vertically connected with the main engine (1) in the radialdirection, and the other ends of the shafts are connected with the ducted fan by being provided with the transmissions, wherein each ducted fan is composed of a transmission shaft, a commutator, a fan shaft and a fan body in a successively connected mode. The two ends of each transmission shaft are correspondingly connected with the transmissions and the commutator, and the commutator is connected with the fan bodies through the fan shafts. The shafts extract power from the main engine (1), and transit the power to the transmission shafts through the transmissions. The transmission shafts areconnected with the fan shafts by the commutator, and the fan shafts are used to drive the fans to realize the driving of the main engine (1) to the ducted fan. The propulsion system efficiency is improved, the high speed flight needs of aircraft are met, the propulsion system is easier to choose a mounting position, and the implementable function of the propulsion system is increased.

Description

technical field [0001] The invention belongs to the field of aeroengine structure design, and in particular relates to a distributed aeropropulsion system. Background technique [0002] In the design of aeroengines, the propulsion efficiency is generally improved by increasing the bypass ratio. The existing low-bypass ratio engines and high-bypass-ratio engines are basically consistent with the core engine. By adjusting the low-pressure components, such as increasing the number of low-pressure turbine stages and expanding the diameter of the fan, the bypass ratio of the engine can be increased, thereby improving Boost efficiency. However, the existing technical solutions have the following disadvantages: with the increase of the bypass ratio of the engine, its outer dimensions increase accordingly. On the one hand, the flight resistance increases due to the increase of the windward area, which cannot meet the high-speed flight requirements of future passenger aircraft; on t...

AI Technical Summary

Problems solved by technology

However, the existing technical solutions have the following disadvantages: with the increase of the bypass ratio of the engine, its external dimensions increase accordingly. On the one hand, the flight resistance increases due to the increase of the windward area, which cannot meet the high-speed flight requirements of future passenger aircraft; on the other hand, The increase of the outer dimension puts forward stricter requirements on the selection of the engine installation position and method

In addition, the existing solutions can only improve the propulsion efficiency, and the functions are single and limited

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