High-pressure turbine nozzle for a turbojet

Patent metadata

Field	Value
Publication number	US-9328618-B2
Application number	US-201113522163-A
Country	US
Kind code	B2
Filing date	Jan 6, 2011
Priority date	Jan 14, 2010
Publication date	May 3, 2016
Grant date	May 3, 2016

Abstract

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.

First claim

The invention claimed is:

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.

2. A nozzle according to claim 1 , wherein the holes formed in each first sleeve, and the holes formed in the corresponding second sleeve, are in maximum correspondence at a nominal operating temperature corresponding to hot stages of operation of the turbojet.

3. A nozzle according to claim 2 , wherein each vane includes a leading edge cavity first sleeve opening out to an outside of the passage through one platform and a trailing edge cavity first sleeve opening out to the outside of the passage through the other platform, and each leading edge and the trailing edge first cavity houses a corresponding second sleeve.

4. A nozzle according to claim 1 , wherein each vane includes a leading edge cavity first sleeve opening out to an outside of the passage through one platform and a trailing edge cavity first sleeve opening out to the outside of the passage through the other platform, and each leading edge and the trailing edge first cavity houses a corresponding second sleeve.

5. A nozzle according to claim 1 , wherein the first sleeves are made of metal and the second sleeves are made of composite material having a relatively lower coefficient of expansion.

6. A nozzle according to claim 5 , wherein the second sleeves are made of ceramic.

7. A nozzle according to claim 1 , wherein each first sleeve and the second sleeve that it contains are paired.

Assignees

• Grohens Régis
• Royan Renaud Gabriel Constant
• Snecma

Inventors

• Grohens Régis
• Royan Renaud Gabriel Constant

Classifications

• F05D2300/50212

  dissimilar · CPC title

• F05D2270/08

  to produce clean exhaust gases · CPC title

• F05D2220/3212

  the first stage of a turbine · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic