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GAS TURBINE ENGINE FOR AIRCRAFT ENGINE

  • US 20150078908A1
  • Filed: 08/03/2012
  • Published: 03/19/2015
  • Est. Priority Date: 08/04/2011
  • Status: Active Grant
First Claim
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1. ) A gas turbine stator (1) for aircraft engines, the stator comprising a blade array (1b) comprising a plurality of blades constituted by a series of first blades (5a) and a series of second blades (5b), said first blades (5a) having a different geometry from said second blades (5b);

  • characterized in that;

    a) said first and second blades are arranged so as to alternate a single first blade (5a) with a single second blade (5b) for the entire circumference of the stator (1);

    b) said blade array is defined by a plurality of sectors (2;

    13;

    14), each comprising;

    i) an inner curved portion (3) next to the inner curved portions of adjacent sectors so as to form an inner annular end-wall (3a);

    ii) an outer curved portion (4) next to the outer curved portions of adjacent sectors so as to form an outer annular end-wall (4a);

    iii) at least one of said first blades (5a) and at least one of said second blades (5b);

    c) each said sector (2;

    13;

    14) is defined by a body made in one piece.

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