Gas turbine stator
View Patent ↗A gas turbine stator including at least a first injector providing a passage for a main cooling air stream into a pressurized chamber. An evacuation mechanism discharges air coming from an internal labyrinth gland of a first cavity towards a lower-pressure second cavity. A second injector evacuates the air contained in the second cavity towards a main duct. The stator further includes a third injector designed to generate an overpressure close to the internal labyrinth gland in the pressurized chamber.
1. A gas turbine stator comprising:
first injection means for providing a passage for a main cooling air stream into a pressurized chamber;
means for evacuating discharge air coming from an internal labyrinth gland partly delimiting the pressurized chamber of a first cavity towards a lower-pressure second cavity;
second injection means for evacuating the air contained in said second cavity towards a main duct; and
third injection means for generating an overpressure of air close to the internal labyrinth gland in said pressurized chamber,
wherein the first injection means comprises at least one blade for generating a flow of air tangent to a rotor of the gas turbine,
wherein the means for evacuating comprises at least one piercing emerging into the first cavity and into the second cavity, and
wherein each piercing is made in a solid part of one of the blades.
2. A gas turbine stator set forth in claim 1 , wherein the first injection means comprises at least one sloping hole for generating a flow of air with a large component tangent to a rotor of the gas turbine.
3. A gas turbine stator set forth in claim 1 , wherein the means for evacuating comprises at least one piercing emerging into the first cavity and into the second cavity.
4. A gas turbine stator set forth in claim 1 , wherein the internal labyrinth gland comprises at least one friction part, each friction part being held by a support in which is located the first injection means, the support being honeycombed by cavities and blocks of material, the cavities configured to lead to the means for evacuating discharge air and the blocks of material configured to comprise the first, second, and third injection means.
5. A gas turbine stator set forth in claim 4 , wherein the third injection means comprises at least one piercing made through the blocks of material.
6. A gas turbine stator set forth in claim 5 , wherein at least one piercing is made sloping to produce a flow of air with a large component tangent to a rotor of the gas turbine.
7. A gas turbine stator set forth in claim 1 , wherein the third injection means comprises at least one blade for generating a flow of air tangent to a rotor of the gas turbine.
8. A gas turbine stator set forth in claim 1 , wherein said second injection means comprises at least one sloping piercing for producing a flow of air with a large component tangent to a rotor of the gas turbine.
9. A gas turbine stator set forth in claim 1 , wherein said second injection means comprises at least one blade for producing a flow of air tangent to a rotor of the gas turbine.
10. A gas turbine stator set forth in claim 1 , wherein the pressurized chamber is delimited by a harpoon external labyrinth gland, creating at least two cavities, each of the two cavities being partly separated from the second cavity by a solid element, said second injection means emerging into at least one of the two cavities being made in the solid element.
11. A jet engine, comprising the gas turbine stator as set forth in claim 1 .
12. A gas turbine stator comprising:
first injection means for providing a passage for a main cooling air stream into a pressurized chamber;
means for evacuating discharge air coming from an internal labyrinth gland partly delimiting the pressurized chamber of a first cavity towards a lower-pressure second cavity;
second injection means for evacuating the air contained in said second cavity towards a main duct; and
third injection means for generating an overpressure of air close to the internal labyrinth gland in said pressurized chamber,
wherein the pressurized chamber is delimited by a harpoon external labyrinth gland, creating at least two cavities, each of the two cavities being partly separated from the second cavity by a solid element, said second injection means emerging into at least one of the two cavities being made in the solid element.
13. A gas turbine stator set forth in claim 12 , wherein the first injection means comprises at least one blade for generating a flow of air tangent to a rotor of the gas turbine.
14. A gas turbine stator set forth in claim 13 , wherein the means for evacuating comprises at least one piercing emerging into the first cavity and into the second cavity.
15. A gas turbine stator set forth in claim 14 , wherein each piercing is made in a solid part of one of the blades.
16. A gas turbine stator set forth in claim 13 , wherein the means for evacuating comprises at least one piercing emerging into the first cavity and into the second cavity.
17. A gas turbine stator set forth in claim 12 , wherein the first injection means comprises at least one sloping hole for generating a flow of air with a large component tangent to a rotor of the gas turbine.
18. A gas turbine stator set forth in claim 12 , wherein the internal labyrinth gland comprises at least one friction part, each friction part being held by a support in which is located the first injection means, the support being honeycombed by cavities and blocks of material, the cavities configured to lead to the means for evacuating discharge air and the blocks of material configured to comprise the first, second, and third injection means.
19. A gas turbine stator set forth in claim 18 , wherein the third injection means comprises at least one piercing made through the blocks of material.
20. A gas turbine stator set forth in claim 19 , wherein at least one piercing is made sloping to produce a flow of air with a large component tangent to a rotor of the gas turbine.
21. A gas turbine stator set forth in claim 12 , wherein the third injection means comprises at least one blade for generating a flow of air tangent to a rotor of the gas turbine.
22. A gas turbine stator set forth in claim 12 , wherein said second injection means comprises at least one sloping piercing for producing a flow of air with a large component tangent to a rotor of the gas turbine.
23. A gas turbine stator set forth in claim 12 , wherein said second injection means comprises at least one blade for producing a flow of air tangent to a rotor of the gas turbine.
24. A jet engine, comprising the gas turbine stator as set forth in claim 12 .