High bypass ratio turbofan engine and aero engine compression system

Abstract

The invention provides a high bypass ratio turbofan engine and an aero engine compression system. The high bypass ratio turbofan engine and the aero engine compression system can improve the overall supercharging effect of a fan inner duct and an increasing level under the premise of increasing the engine mass as little as possible. The aero engine compression system includes a pre-compression configuration, and the pre-compression configuration is located at the front end of a fan rotor and at the rear end of an air inlet cone; the pre-compression configuration includes a rectifying outer ring, a plurality of blades and an internal flow passage ring, the rectifying outer ring is located at an outer ring, the internal flow passage ring is located at an inner ring, and the multiple blades are located between the outer ring and the inner ring; and the rectifying outer ring, the blades and the internal flow passage ring constitute a contraction passage.

Description

technical field [0001] The present invention relates to aeroengine compression systems. Background technique [0002] At present, in the domestic and foreign aero-engine compression systems, the supercharging stage with the same speed as the fan rotor is mainly used to do work on the gas in the internal channel behind the fan blades. [0003] In order to increase the compression effect, US6173566B1 discloses a pre-compression solution, which is realized by a detachable booster stage. DE 10 2014 226 696 A1 discloses that a precharger is arranged upstream of the fan, but this precharger is also a booster stage consisting of a plurality of blades. The pre-charger used in DE4131713A1 is also in the form of booster stage blades. [0004] The following problems exist in this type of design technique: [0005] Limited by the flow velocity at the tip of the fan blade, the rotor speed of the fan and the booster stage cannot be very high, which makes the boosting effect of the gas ...

AI Technical Summary

Problems solved by technology

[0005] Limited by the flow velocity at the tip of the fan blade, the rotor speed of the fan and the booster stage cannot be very high, which makes the boosting effect of the gas pass through the booster stage poor; if the outlet pressure ratio of the booster stage is increased, the booster has to be increased The number of stages, resulting in an increase in the axial size of the fan booster stage, which in turn increases the engine mass

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