Patent ID: 9599020
Date: 2017-03-21
CPC Classifications: F01D,F02C,F05B,F05D,Y02T

Claim:
1. A sectorized nozzle for a turbine engine turbine comprising: an inner sectorized annular platform and an outer sectorized annular platform connected together by substantially radial airfoils, at least one of the platforms including a plurality of through orifices for passing air upstream of a leading edge of the airfoils, the through orifices being distributed over the circumference of the platform, wherein the through orifices for passing air in each sector of a platform open out upstream from the airfoils into a circumferential annular cavity of the sector of the platform, the cavity being closed and further comprising cooling air feed orifices that are offset tangentially in a staggered configuration relative to the through orifices in the platform, wherein the cavity is formed by a groove arranged in a thickness of the at least one of the platforms of each nozzle sector and closed by a metal sheet including the cooling air feed orifices, wherein the cavity is disposed downstream of a radial wall of the at least one of the platforms, and a sealing device is fastened to the radial wall, and wherein the metal sheet being inserted radially between the radial wall and a radial tab of the sealing device.