Rotor blades for turbine engines

Rotor blades for turbine engines

  • CN 105,065,064 A
  • Filed: 04/16/2010
  • Published: 11/18/2015
  • Est. Priority Date: 04/17/2009
  • Status: Active Application
First Claim
Patent Images

1. the blade tips for the turbine rotor blade of gas turbine engine, described turbine rotor blade comprise airfoil and for by described airfoil radially axis be installed to inside turbine shroud rotor disk on root portion, the pressure sidewall linked together in leading edge and trailing edge place and suck sidewall, described pressure sidewall and described suction sidewall extend to described blade tips from described root portion, and be formed in the squealer tip chamber at described blade tips place, described blade tips comprises:

  • Originate in the trailing edge groove of the rear end in described squealer tip chamber, wherein, described trailing edge groove extends towards the trailing edge of described blade tips;

    Described blade tips is included in the end plate extended between the radially outer edge of described pressure sidewall and the radially outer edge of described suction sidewall;

    Described squealer tip chamber is formed by pressure tip wall in the first side, and described pressure tip wall extends radially outward from described end plate, is transverse to described trailing edge from described leading edge, makes described pressure tip wall be positioned near the terminal of described pressure sidewall;

    Described squealer tip chamber is formed by sucking tip wall in the second side, and described suction tip wall extends radially outward from described end plate, is transverse to described trailing edge from described leading edge, makes described suction tip wall be positioned near the terminal of described suction sidewall;

    Wherein, the width of described trailing edge groove reduces gradually when described groove extends from described squealer tip chamber towards the trailing edge of described blade tips;

    AndWherein, described trailing edge groove is located so that described trailing edge groove compared to described suction sidewall closer to described pressure sidewall.

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