Blade with a cooling groove for a bladed wheel of a turbomachine
View Patent ↗A blade for a turbomachine bladed wheel is disclosed. The blade includes an airfoil and a platform with at least one air injection passage. The platform including includes a groove running along the pressure side of the airfoil at least in the vicinity of a downstream portion thereof, and formed between the pressure side and a ridge formed on the platform surface at a short distance from the downstream portion of the pressure side. At least one air injection passage is arranged in the groove. Because of the presence of the groove, the air stream injected via the air injection passage(s) is kept close to the pressure side and thus provides effective cooling of the downstream portion thereof.
1. A blade for a turbomachine bladed wheel, the blade comprising:
an airfoil having a pressure side and a platform extending from one of the ends of the airfoil in a direction that is generally perpendicular to a longitudinal direction of the airfoil, the platform including at least one air injection passage, and a groove running along the pressure side in the vicinity at least of a downstream portion of the airfoil and formed between the pressure side and a ridge formed on the platform surface at a short distance from said downstream portion of the pressure side,
wherein said at least one air injection passage is formed in said groove, and
wherein the ridge projects above the platform surface towards a free end of the airfoil.
2. The blade according to claim 1 , wherein the blade is suitable for being placed together with a plurality of substantially identical blades to form a ring around a ring axis in which the airfoils are disposed substantially radially, the platform surface in the vicinity of a downstream portion of the pressure side is substantially a surface of revolution about the axis of the ring, and the groove is formed as a depression relative to said surface.
3. The blade according to claim 1 , wherein the groove is defined on one side by the pressure side and on the other side by the ridge.
4. The blade according to claim 1 , wherein the groove extends relative to a neutral fiber of the airfoil from a first quarter of the airfoil to a point of the airfoil that is furthest downstream.
5. The blade according to claim 1 , wherein the groove has multiple air injection passages distributed along the groove.
6. A bladed wheel including a plurality of blades, wherein each blade is structured according to claim 1 .
7. A turbomachine including at least one bladed wheel according to claim 6 .
8. A blade for a turbomachine bladed wheel, the blade comprising:
an airfoil having a pressure side and a platform extending from one of the ends of the airfoil in a direction that is generally perpendicular to a longitudinal direction of the airfoil, the platform including at least one air injection passage, and a groove running along the pressure side in the vicinity at least of a downstream portion of the airfoil and formed between the pressure side and a ridge formed on the platform surface at a short distance from said downstream portion of the pressure side,
wherein said at least one air injection passage is formed in said groove,
wherein the blade is suitable for being placed together with a plurality of substantially identical blades to form a ring around a ring axis in which the airfoils are disposed substantially radially, the platform surface in the vicinity of a downstream portion of the pressure side is substantially a surface of revolution about the axis of the ring, and the groove is formed as a depression relative to said surface, and
wherein the ridge projects above the platform surface towards a free end of the airfoil, and the at least one air injection passage is pointed toward the pressure side of the airfoil.
9. The blade according to claim 8 , wherein the groove is defined on one side by the pressure side and on the other side by the ridge.
10. The blade according to claim 8 , wherein the groove extends relative to a neutral fiber of the airfoil from a first quarter of the airfoil to a point of the airfoil that is furthest downstream.
11. The blade according to claim 8 , wherein the groove has multiple air injection passages distributed along the groove.
12. A bladed wheel including a plurality of blades, wherein each blade is structured according to claim 8 .
13. A turbomachine including at least one bladed wheel according to claim 12 .