High-pressure turbine nozzle for a turbojet

摘要

A high temperature turbine nozzle with automatic regulation of flow of cooling air passing therethrough. Each of vanes includes a first sleeve drilled with holes and a second sleeve that is engaged in the first sleeve, drilled with corresponding holes, and made of a material possessing a coefficient of expansion different from that of the first sleeve.

主权项

1. A nozzle for a high-pressure turbine of a turbojet, the nozzle comprising:
a ring of stationary and hollow vanes arranged between first and second coaxial annular platforms defining a gas flow passage and in which each vane includes at least one cavity housing a first sleeve including a first end opening out to an outside of the passage through one of the platforms and including an end wall at a second end, the first sleeve being drilled by a plurality of holes opening out into the cavity, wherein a second sleeve of material possessing a coefficient of expansion different from that of the first sleeve is engaged inside the first sleeve and is shaped so that an outside wall of the second sleeve is substantially in contact with an inside wall of the first sleeve, wherein the second sleeve is drilled by a plurality of holes substantially in correspondence with the holes of the first sleeve, one end of the second sleeve being fastened to the end wall of the first sleeve, and wherein the holes of the second sleeve are in partial alignment with the holes of the first sleeve at a first temperature, and the holes of the second sleeve are in maximum alignment with the holes of the first sleeve at a second temperature higher than the first temperature.