Fan blade disc structure and turbofan engine

Abstract

The invention provides a fan blade disc structure and a turbofan engine. The fan blade disc structure comprises a main fan blade and an auxiliary fan blade, the longitudinal section of the shunting ring is of an I-shaped structure, the shunting ring comprises a shroud ring, an extending radial plate and a blade tip fan edge plate, the shroud ring is fixedly connected with the outer edge of the main fan blade, and the two ends of the extending radial plate are connected with the shroud ring and the blade tip fan edge plate respectively; the inner edge of the blade tip fan blade is fixedly connected with the blade tip fan edge plate; and the fiber reinforced ring is arranged on the hoop ring in a sleeving manner. The fan blade has the beneficial effects that the centrifugal force of the shunting ring and the blade tip fan blade is borne through the fiber reinforcing ring, the radial elongation of the main fan blade is limited, the stress state of the air inlet side and the air outlet side of the main fan blade is changed into partial pressure stress from tensile stress, and therefore the blade profile thickness and the stress level of the main fan blade are reduced.

Description

technical field [0001] The invention relates to the field of aviation turbofan engines, in particular to a fan blade disc structure and the turbofan engine. Background technique [0002] As one of the many layouts of variable cycle engines, the adaptive variable cycle engine with blade tip fan (that is, FLADE engine) mainly adopts the key technology of adaptive fan, that is, the airflow passes through the third duct on demand, allowing the engine to to change the bypass ratio. And the airflow of the third outer confinement (ie, the third stream) is used to increase or decrease the bypass ratio of the engine or to cool it. The FLADE engine can achieve a greater variable cycle through the coordinated adjustment of multiple adjustable mechanisms including the blade tip fan, so as to adapt to the different performance requirements of the engine during supersonic cruise, transonic and subsonic cruise flights. It is an ideal candidate for the next generation of fighter jets. ...

AI Technical Summary

Problems solved by technology

[0005] One is the strength of the overall blisk of the fan with the blade tip rotor, which mainly affects the structural integrity and reliability of the adaptive fan components

In the state of high-speed rotation, the splitter ring must transmit the centrifugal force of itself and the tip fan blades to the disc through the main fan blades, which will inevitably cause high stress on the inlet and outlet sides of the main fan blades, especially the main fan blades. The connection between the tip and the shunt ring cannot even meet the static strength design requirements

The traditional solution is to thicken the blade shape, increase the thickness of the shunt ring and the size of the tip rounding, etc., which will significantly increase the weight of the rotor, and seriously affect the aerodynamic performance of the main fan, and ultimately cannot meet the development needs of fan components

[0006] The second is the realization of the sealing structure on the splitter ring, which mainly affects the aerodynamic performance of the blade tip fan

Traditional grate seals, brush seals and other sealing structures require a large design space, requiring a larger height and width space for the splitter ring, and the higher the radial position of the splitter ring and blade tip fan, the greater the impact on the overall blisk. the more unfavorable the strength

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