Distributed propulsion system

Abstract

The invention discloses a distributed propulsion system. The distributed propulsion system is characterized in that input ends of gas collecting devices of a high-energy working medium collecting device are communicated with an output end of a core machine gas compressor of a turbine engine core machine; output ends of the high-energy working medium collecting device are communicated with inlets of efficient working medium transmission devices; output ends of transmission branched pipes of the efficient working medium transmission devices are respectively communicated with input ends of propeller turbine volute casings of various distributed propellers; input ends of the transmission branched pipes are communicated with transmission header pipes of the efficient working medium transmission devices; the six distributed propellers are uniformly distributed on two sides of the turbine engine core machine. The distributed propulsion system has the advantages that the shortcoming of dependence of distributed propulsion systems on the basis of electric power distribution on energy storage equipment with high energy density and super-power motors can be overcome, and the implementability of the distributed propulsion system can be enhanced; mechanical restraint between gas generators and propellers in a distributed propulsion system on the basis of mechanical transmission can be dispensed, bypass ratio limit on turbo fan engines and the traditional distributed power can be broken through, the distributed propulsion system is in a heat regenerative design, and the propulsion efficiency can be improved.

Description

technical field [0001] The invention relates to an aviation propulsion system, in particular to a distributed propulsion system. Background technique [0002] Economy is a key factor to be considered for transport aircraft. At the same time, as environmental problems continue to become prominent, people are also putting forward more and more stringent requirements for reducing carbon emissions. This all requires improving the efficiency of the existing transporter power (turbofan engine). One of the effective measures to improve turbofan engine efficiency is to use a higher bypass ratio to obtain high propulsion efficiency. The bypass ratio of the current civil turbofan engine is close to 10, but it is difficult to further improve it due to the limitation of structure and component matching. The distributed propulsion system breaks through the structural and component matching limitations of the traditional turbofan engine, so a higher bypass ratio can be obtained. At the...

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Problems solved by technology

[0010]In order to overcome the existing energy storage equipment and motor power that cannot meet the demand based on power distribution in the prior art; when based on mechanical transmission, the mechanical transmission mechanism is complicated, The weight is large, which is not conducive to the lack of layout on the aircraft. This invention proposes a distributed propulsion system

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