Compressor bleed structure and aero-engine

Abstract

The present disclosure relates to a compressor bleed structure and an aeroengine. Among them, the air-inducing structure of the compressor includes: two-stage rotor discs; two-stage rotor blades; a drum with a plurality of air-introduction ports distributed along the circumferential direction; On the outer wall of the drum and at the same axial position as the air inlet, it is used to guide the air flow and guide it to the air inlet. Every two guide vanes are respectively arranged at both ends of an air inlet; wherein, the air guide The offset direction of the blades is configured to coincide with the rotation direction of the rotor disk. The guide vane can rectify the turbulent flow field near the air-induction port and lead it to the air-induction port. Compared with the structure with guide vanes at one end, it can effectively reduce the flow loss of the air-induction and improve the efficiency of the air-induction.

Description

technical field [0001] The disclosure relates to the technical field of gas turbines, in particular to a compressor bleed air structure and an aeroengine. Background technique [0002] In an aero-engine compressor, the rotor-stator part of the turbine with a relatively high operating temperature usually needs to be cooled by introducing cold air from the compressor end with a relatively low operating temperature. Flow through the inner cavity of the rotor to the turbine end, and usually directly open holes on the wall of the rotor drum to guide the cooling air with a certain pressure in the main channel of the compressor to the inner cavity of the rotor, but there are the following problems in this design technology: [0003] 1. Most of the air-inducing ports on the drum wall are located in the concave cavity between the stages. The flow field at this position is affected by its position and shape, which is extremely disordered and the air-inducing efficiency is low; [000...

AI Technical Summary

Problems solved by technology

[0003] 1. Most of the air-inducing ports on the drum wall are located in the concave cavity between the stages. The flow field at this position is affected by its position and shape, which is extremely disordered and the air-inducing efficiency is low;

[0004] 2. Generally, the air-induction ports on the drum wall are distributed along the circumferential interval and rotate with the rotor. Although the air flow at the air-induction port has a certain circumferential speed, the circumferential speed is lower than the circumferential rotation speed of the air-induction port. The loss of bleed air flow is further aggravated when it flows to the bleed air port with a relatively high speed of movement, reducing the bleed air efficiency

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