Multistage axial compressor with front-stage stator and rear-stage stator self-adaptive air blowing and sucking

Multistage axial compressor with front-stage stator and rear-stage stator self-adaptive air blowing and sucking

  • CN 107,191,412 B
  • Filed: 07/24/2017
  • Issued: 10/23/2020
  • Est. Priority Date: 07/24/2017
  • Status: Active Grant
First Claim
Patent Images

1. The utility model provides a multistage axial compressor of preceding back stage stator self-adaptation air blowing and suction which characterized in that:

  • the turbine rotor blade structure comprises a front-stage stator blade, a rotor blade, a rear-stage stator blade, a casing and a gas-guiding pipe structure positioned in the casing, wherein the front-stage stator blade is fixed at the upstream of the casing along the incoming flow direction and is provided with a jet flow groove structure;

    the rotor blade is positioned at the downstream of the stator blade of the front stage, and a blade top gap is formed between the rotor blade and the casing;

    the stator blade of the rear stage is positioned at the downstream of the rotor blade and is provided with a suction groove structure;

    the suction groove of the stator blade at the rear stage is communicated with the jet groove of the stator blade at the front stage through an air entraining pipe positioned in the casing;

    one or more rotor blade rows between the stator blades of the front stage and the stator blades of the rear stage;

    the air guide pipe in the casing is strictly sealed and has an annular array structure, and the number of the air guide pipe is equal to that of the stator blades of the previous stage;

    the rear-stage stator blade casing side and hub side suction surfaces are respectively provided with a plurality of suction grooves along the spanwise direction, the width of each suction groove is 2% of the chord length of the blade, the height of each suction groove does not exceed 20% of the spanwise height of the blade, the rear-stage stator blade casing end wall and the hub end wall are respectively provided with a single suction groove from the tail edge along 25% of the axial chord length in the flowing direction close to the suction surface side, and the groove width is 2% to 5% times of the chord length value of the blade.

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