Cooled gas turbine engine vane
View Patent ↗A cooled gas turbine vane includes a cast part and a longitudinal sleeve obtained by shaping metal sheet The cast part includes a longitudinal body provided with a longitudinal cavity having a first opening and a second opening at the ends The sleeve is mounted in the cavity by being firmly affixed to the wall of the first opening, and one end part of which being free to slide in the second opening forming a guide. The end part includes a part having constricted dimensions relative to the transverse dimensions of the guide.
1. A cooled gas turbine engine vane comprising a cast part and a longitudinal sleeve, for guiding the flow of cooling air, obtained by shaping sheet metal, the cast part comprising a longitudinal body provided with a longitudinal cavity having a first opening for feeding and a second opening for evacuation of air at the extremities, the sleeve being mounted in the cavity, by being attached to the wall of the first opening, one end part of which being free to slide into the second opening forming a guide, wherein said end part guided by the guide comprises a constriction of its passage crossing-section for the air flow, wherein a dimension of said constriction diminishes while extending away from the cavity.
2. The vane according to claim 1 , wherein the sleeve is attached to the wall of the first opening by welding or by brazing.
3. The vane according to claim 1 , wherein the constriction is obtained by folding the end of the sleeve.
4. The vane according to claim 3 , wherein the folding is of curved profile section.
5. The vane according to claim 1 , wherein the sleeve is perforated.
6. The vane according to claim 5 , wherein the cast part comprises calibrated perforations.
7. A cooled gas turbine engine vane comprising:
a cast part comprising a longitudinal body defining a longitudinal cavity with a first opening and a second opening;
a longitudinal sleeve made of sheet metal and configured to guide a flow of cooling air, said sleeve being mounted in said cavity and attached to a wall of the first opening, and said sleeve having an end part that is free to slide into the second opening; and
means for forming an air flow constriction at said end part of said sleeve and for reducing static pressure at an outlet of said sleeve,
wherein said means have a dimension that diminishes away from the cavity.
8. The vane according to claim 7 , wherein said means comprise a folded portion of said end part of the sleeve.
9. The vane according to claim 7 , wherein said means comprise a perforated plate.
10. The vane according to claim 7 , wherein the sleeve is perforated.
11. The vane according to claim 7 , wherein the cast part comprises calibrated perforations.
12. A cooled gas turbine engine vane comprising:
a cast part comprising a longitudinal body defining a longitudinal cavity with a first opening and a second opening;
a longitudinal sleeve made of sheet metal and configured to guide a flow of cooling air, said sleeve being mounted in said cavity and attached to a wall of the first opening, and said sleeve having an end part that is free to slide into the second opening:
means for forming an air flow constriction at said end part of said sleeve and for reducing static pressure at an outlet of said sleeve; and
wherein said means comprise a tube having a conical shape and cross-section dimensions that diminish away from the cavity.
13. A cooled gas turbine engine vane comprising:
a cast part comprising a longitudinal body defining a longitudinal cavity with a first opening and a second opening;
a longitudinal sleeve made of sheet metal and configured to guide a flow of cooling air, said sleeve being mounted in said cavity and attached to a wall of the first opening, and said sleeve having an end part that is free to slide into the second opening; and
a tube attached to said end part of the sleeve and forming an air flow constriction, wherein the tube has a conical shape, whose cross-section dimensions diminish while extending from the end part of the sleeve.