Gas turbine engine blade squealer pockets
A blade for a gas turbine engine includes an airfoil having a tip with a terminal end surface and multiple squealer pockets recessed into the terminal end surface. A method of cooling a blade includes the steps of providing cooling fluid to a first squealer pocket in an airfoil tip, and providing cooling fluid to a second squealer pocket in the airfoil tip in an amount that is different than that provided to the first squealer pocket.
1. A blade for a gas turbine engine comprising:
an airfoil extending in a radial direction to a tip with a terminal end surface, and multiple squealer pockets recessed into the terminal end surface, wherein one of the squealer pockets has a first depth near the leading edge that is different than a second depth located aftward of the first depth, wherein a continuous perimeter surface is parallel with the radial direction and circumscribes without interruption an entirety of the one of the squealer pockets, and the terminal end surface adjoins the perimeter surface.
2. The blade according to claim 1 , wherein the terminal end surface provides a perimeter wall circumscribing the tip, the squealer pockets arranged interiorly of the perimeter wall.
3. The blade according to claim 2 , wherein the tip includes at least one intermediate wall interconnecting opposing sides of the perimeter wall and separating adjoining squealer pockets.
4. The blade according to claim 3 , wherein the intermediate wall extends in a thickness direction between pressure and suction sides of the airfoil.
5. The blade according to claim 1 , wherein the airfoil includes at least one cooling passage arranged interiorly, and cooling holes fluidly connect the at least one cooling passage to the squealer pockets.
6. The blade according to claim 1 , wherein the squealer pockets have a depth of at least 20 mils (0.50 mm).
7. The blade according to claim 1 , wherein one of the squealer pockets is arranged near the leading edge.
8. A gas turbine engine comprising:
compressor and turbine sections; and
an airfoil provided in one of the compressor and turbine sections, the airfoil extending in a radial direction to a tip with a terminal end surface, and multiple squealer pockets recessed into the terminal end surface, wherein one of the squealer pockets has a first depth near the leading edge that is different than a second depth located aftward of the first depth, wherein a continuous perimeter surface extends radially inwardly relative to the terminal end surface about the entire circumference of the one of the squealer pockets and without interruption, and the terminal end surface adjoins the perimeter surface.
9. The gas turbine engine according to claim 8 , wherein the turbine section includes a turbine blade having the airfoil.
10. The gas turbine engine according to claim 8 , wherein the terminal end surface provides a perimeter wall circumscribing the tip, the squealer pockets arranged interiorly of the perimeter wall.
11. The gas turbine engine according to claim 10 , wherein the tip includes at least one intermediate wall interconnecting opposing sides of the perimeter wall and separating adjoining squealer pockets.
12. The gas turbine engine according to claim 11 , wherein the intermediate wall extends in a thickness direction between pressure and suction sides of the airfoil.
13. The gas turbine engine according to claim 8 , wherein the airfoil includes at least one cooling passage arranged interiorly, and cooling holes fluidly connect the at least one cooling passage to the squealer pockets.
14. The gas turbine engine according to claim 8 , wherein the squealer pockets have a depth of at least 20 mils (0.50 mm).
15. The gas turbine engine according to claim 8 , wherein one of the squealer pockets is arranged near the leading edge.
16. A method of cooling a blade comprising the steps of:
providing cooling fluid to a first squealer pocket in an airfoil tip; and
providing cooling fluid to a second squealer pocket in the airfoil tip in an amount that is different than that provided to the first squealer pocket, wherein one of the first and second squealer pockets includes a stepped bottom surface, wherein a continuous perimeter surface is parallel with a radial direction of the blade and circumscribes without interruption an entirety of the one of the first and second squealer pockets, and a terminal end surface of the airfoil tip adjoins the perimeter surface.
17. The method according to claim 16 , wherein the first and second squealer pockets are arranged adjacent to one another.
18. The method according to claim 16 , wherein the first squealer pocket is arranged near an airfoil leading edge.
19. The method according to claim 18 , wherein the first squealer pocket is provided more cooling fluid than the second squealer pocket.