Tip squealer configurations

Patent metadata

Field	Value
Publication number	US-11299991-B2
Application number	US-202016850661-A
Country	US
Kind code	B2
Filing date	Apr 16, 2020
Priority date	Apr 16, 2020
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

The present embodiments set forth a blade including an airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the tip cap. The airfoil further includes a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall and around the leading edge and trailing edge. The tip cap includes a squealer tip configuration including a suction side tip cap portion and a pressure side tip cap portion. The suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor providing for cooling fluid flow out of the tip cap.

First claim

What is claimed is:

1. A blade, the blade comprising:
an airfoil including an outer tip, the outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the outer tip;
the airfoil further including:
a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall around each of the leading edge and trailing edge, the tip cap including a squealer tip configuration to reduce overtip leakage and downstream mixing loss, and the squealer tip configuration includes a suction side tip cap portion at a first elevation and a pressure side tip cap portion at a second elevation; wherein the tip cap includes an offset providing a decreasing elevation change from the first elevation of the suction side tip cap portion to the second elevation of the pressure side tip cap portion;
wherein the suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor, wherein the pressure side tip cap portion includes the offset providing the decreasing elevation change from the first elevation of the suction side tip cap portion to the second elevation of the pressure side tip cap portion, the offset including a step-down section from the first elevation of the suction side tip cap portion to the second elevation of the pressure side tip cap portion, and cooling fluid flow is over the pressure side tip cap portion of the tip cap due to pressure gradients, wherein the step-down section of the pressure side tip cap portion extends substantially the entire pressure side tip cap portion and wherein the offset from the first elevation of the suction side tip cap portion to the second elevation of the pressure side tip cap portion is selected from at least one of a sloped decreasing elevation change, a convex curved decreasing elevation change, a concave curved decreasing elevation change, or combinations thereof.

2. The blade according to claim 1 , wherein the suction side tip cap portion extends above the floor a greater distance than the pressure side tip cap portion, wherein cooling fluid flow is over of the pressure side tip cap portion of the tip cap.

3. The blade according to claim 2 , wherein the offset is positioned proximate the leading edge to transition the tip cap from the suction side tip cap portion to the step-down section of the pressure side tip cap portion.

4. The blade according to claim 3 , wherein the elevation change is about less about 100 mils.

5. The blade according to claim 3 , wherein the elevation change is less about 50 mils.

6. The blade according to claim 3 , wherein the elevation change is in a range from about 10 mils to about 50 mils.

7. The blade according to claim 3 , wherein the offset is formed on one of: the pressure side tip cap portion; the leading edge; or the pressure side tip cap portion at the leading edge; or the pressure side tip cap portion proximate the leading edge.

8. The blade according to claim 1 , further including an opening at the trailing edge for exhaust of cooling fluid flow.

9. The blade according to claim 8 , wherein the opening is formed in the pressure side tip cap portion and extends from the trailing edge towards the leading edge.

10. The blade according to claim 1 , the tip cap includes a cavity between the floor, the suction side tip cap portion, and pressure side tip cap portion; the blade including at least one internal cooling fluid passage leading to at least one corresponding cooling fluid hole in the floor.

11. The blade according to claim 10 , further including an opening in tip cap for exhaust of cooling fluid flow out of the cavity, wherein the opening is formed proximate the trailing edge in the pressure side tip cap portion.

12. A turbine engine, the turbine engine comprising:
a blade, the blade including an airfoil,
the airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the outer tip, the airfoil further including:
a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall around each of the leading edge and trailing edge, the tip cap including a squealer tip configuration, the squealer tip configuration configured to reduce overtip leakage and downstream mixing loss, and includes a suction side tip cap portion at a first elevation and a pressure side tip cap portion at a second elevation;
wherein the suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor, wherein the pressure side tip cap portion includes the offset providing the decreasing elevation change from the first elevation of the suction side tip cap portion to the second elevation of the pressure side tip cap portion, the offset including a step-down section from the first elevation of the suction side tip cap portion to the second elevation of the pressure side tip cap portion, cooling fluid flows over the pressure side tip cap portion of the tip cap due to a pressure gradient, and
wherein the offset being positioned proximate the leading edge to transition the tip cap from the suction side tip cap portion to the step-down section of the pressure side tip cap portion; wherein the step-down section of the pressure side tip cap portion extends substantially the entire pressure side tip cap portion and wherein the offset from the first elevation of the suction side tip cap portion to the second elevation of the pressure side tip cap portion is selected from at least one of a sloped decreasing elevation change, a convex curved decreasing elevation change, a concave curved decreasing elevation change, or combinations thereof.

13. The turbine engine according to claim 12 , wherein the elevation change is about less about 100 mils.

14. The turbine engine according to claim 12 , wherein the elevation change is in a range from about 10 mils to about 50 mils.

15. The turbine engine according to claim 12 , wherein the offset is formed on one of: the pressure side tip cap portion; the leading edge; or the pressure side tip cap portion at the leading edge; or the pressure side tip cap portion proximate the leading edge.

16. The turbine engine according to claim 12 , further including an opening in the trailing edge for exhaust of cooling fluid flow out of the tip cap.

17. The turbine engine according to claim 12 , the tip cap includes a cavity between the floor and the suction side tip cap portion and pressure side tip cap portion, the blade including at least one internal cooling fluid passage leading to corresponding at least one cooling fluid hole in the floor.

Assignees

• Gen Electric

Inventors

• Ristau Neil Devin
• Wondrasek Michael Anthony

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2250/712

  concave · CPC title

• F01D5/189

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F05D2250/314

  the axes being inclined in relation to each other · CPC title