A Double Radial Sealing Structure Used Between Compressor Stages

Abstract

The invention discloses a dual radial sealing structure for compressor interstage, and belongs to the field of aeroengine compressor application. Air currents pass through a first radial sealing section and a second radial sealing section after passing through an inlet axial sealing section; the two radial sealing sections consist of three baffle plates; one baffle plate is machined on a stator crown, and the other two baffle plates are arranged on a compressor hub; the three annular baffle plates are rectangular on peripheral sections; the side ends of the baffle plates are filleted; the three baffle plates are different in radial height, and are alternately arranged in different radial positions to form the dual radial sealing structure; and meanwhile, two annular baffle plates on the hub are rotated to enlarge rotary currents of an inlet rotary static disc cavity for stopping flowing of leaked currents. The dual radial sealing structure is easy to realize machining. The dual radialsealing structure stops the air currents from flowing in through dual sealing of the baffle plates and radial gaps, increases the flowing resistance of the air currents, can effectively reduce the compressor interstage leakage flow, and improves the compressor efficiency.

Description

technical field [0001] The invention relates to the technical field of application of aero-engine compressors, in particular to a double radial sealing structure used between compressor stages. Background technique [0002] In aeroengines, compressors often use crowned stator blades to prevent excessive vibration of the blades. Generally, there are slots on the rotor hub to accommodate the stator crowns. Usually, the area between the rotor and the stator inside the main flow channel is called For the compressor stage. As the main flow pressure of the compressor increases, the gas flow will leak back through the stages. In order to prevent excessive airflow from leaking from the interstage gap, grate teeth are often used to seal between the rotor hub and the stator crown. This air flow will cause the main flow to decrease, interfere with the aerodynamic characteristics of the main flow of the compressor, and reduce the efficiency of the compressor. In addition, the wind re...

AI Technical Summary

Problems solved by technology

However, if the gap is too small, the temperature rise of the air flow between the stages is serious, which makes the temperature of the rotor stator between the stages rise significantly. The highest temperature of the wall surface at the interstage position of the high-pressure compressor will reach 120K higher than the temperature of the mainstream gas of the compressor as measured by experiments.

The temperature rise is large, the deformation of the rotor and the stator is large, and the grate teeth and the stator are prone to serious scratches, which will reduce the life of the compressor and even cause danger

In addition, due to the high linear velocity of the rotor and the high temperature of the airflow, the application of new sealing structures such as brush seals is also quite difficult.

[0004] With the continuous improvement of the engine cycle parameters, it is very difficult to reduce the interstage leakage flow and improve the compressor efficiency only by reducing the tooth tip clearance of the grate tooth

Images