Airfoil having dead-end tip flag cavity

Patent metadata

Field	Value
Publication number	US-11168571-B2
Application number	US-202016745930-A
Country	US
Kind code	B2
Filing date	Jan 17, 2020
Priority date	Feb 8, 2019
Publication date	Nov 9, 2021
Grant date	Nov 9, 2021

Abstract

Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, the airfoil comprising:
an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side;
a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity;
a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body, wherein the dead-end tip flag cavity is defined by an outer wall, an inner wall, and the dead-end wall, with the outer wall and the inner wall extending in a direction between the leading edge and the trailing edge and the dead-end wall extending in a direction between the platform and the tip; and
a squealer pocket arranged at the tip of the airfoil body, wherein the outer wall of the dead-end tip flag cavity forms a pocket surface of the squealer pocket,
wherein the dead-end tip flag cavity, the down-pass serpentine cavity of the serpentine cavity, and the squealer pocket end at the same axial position in a direction between the leading edge and the trailing edge of the airfoil body.

2. The airfoil of claim 1 , further comprising at least one bleed hole arranged to fluidly connect the dead-end tip flag cavity and the serpentine cavity, the at least one bleed hole formed in the inner wall of the dead-end tip flag cavity.

3. The airfoil of claim 1 , further comprising at least one tip cooling hole formed within the outer wall and configured to enable fluid connection between the dead-end tip flag cavity and the squealer pocket.

4. The airfoil of claim 1 , further comprising a leading edge cavity extending in a direction from the platform to the tip and arranged along the leading edge of the airfoil body.

5. The airfoil of claim 4 , wherein the leading edge cavity and the dead-end tip flag cavity are fluidly connected.

6. The airfoil of claim 1 , wherein the trailing edge cavity includes an outer most trailing edge slot proximate to the tip and having a radial height, wherein a radial height of the dead-end tip flag cavity is equal to the radial height of the outer most trailing edge slot.

7. The airfoil of claim 1 , wherein the down-pass serpentine cavity of the serpentine cavity is defined in part by an aft down pass rib and wherein the dead-end wall of the dead-end cavity are aligned in a direction from the platform to the tip.

8. A gas turbine engine comprising:
a turbine section having a plurality of airfoils, wherein at least one airfoil comprises a blade having:
an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side;
a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity;
a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body, wherein the dead-end tip flag cavity is defined by an outer wall, an inner wall, and the dead-end wall, with the outer wall and the inner wall extending in a direction between the leading edge and the trailing edge and the dead-end wall extending in a direction between the platform and the tip; and
a squealer pocket arranged at the tip of the airfoil body, wherein the outer wall of the dead-end tip flag cavity forms a pocket surface of the squealer pocket,
wherein the dead-end tip flag cavity, the down-pass serpentine cavity of the serpentine cavity, and the squealer pocket end at the same axial position in a direction between the leading edge and the trailing edge of the airfoil body.

9. The gas turbine engine of claim 8 , further comprising at least one bleed hole arranged to fluidly connect the dead-end tip flag cavity and the serpentine cavity, the at least one bleed hole formed in the inner wall of the dead-end tip flag cavity.

10. The gas turbine engine of claim 8 , further comprising a leading edge cavity extending in a direction from the platform to the tip and arranged along the leading edge of the airfoil body, wherein the leading edge cavity and the dead-end tip flag cavity are fluidly connected.

11. The gas turbine engine of claim 8 , wherein the trailing edge cavity includes an outer most trailing edge slot proximate to the tip and having a radial height, wherein a radial height of the dead-end tip flag cavity is equal to the radial height of the outer most trailing edge slot.

12. The gas turbine engine of claim 8 , wherein the down-pass serpentine cavity of the serpentine cavity is defined in part by an aft down pass rib and wherein the dead-end wall of the dead-end cavity are aligned in a direction from the platform to the tip.

13. A core assembly for the formation of an airfoil for a gas turbine engine, the core assembly comprising:
a serpentine cavity core configured to form a serpentine cavity in a formed airfoil, the serpentine cavity core having an up-pass serpentine cavity core, a down-pass serpentine cavity core, and a trailing edge cavity core; and
a dead-end tip flag cavity core positioned relative to the serpentine cavity core, the dead-end tip flag cavity core extending in a direction between a leading edge and a trailing edge of the formed airfoil, the dead-end tip flag cavity core arrange between the serpentine cavity core and a tip location of the formed airfoil, wherein the dead-end tip flag cavity core ends at a dead-end located at a position between the leading edge and the trailing edge of the formed airfoil,
wherein the dead-end tip flag cavity core is configured to form a dead-end tip flag cavity in the formed airfoil, wherein the formed dead-end tip flag cavity is defined by an outer wall, an inner wall, and the dead-end wall, with the outer wall and the inner wall extending in a direction between the leading edge and the trailing edge and the dead-end wall extending in a direction between the platform and the tip; and
a squealer pocket core arranged radially outward from the dead-end tip flag cavity core, wherein squealer pocket core is configured to form a squealer pocket and the outer wall of the formed dead-end tip flag cavity forms a pocket surface of the squealer pocket,
wherein the dead-end tip flag cavity core, the down-pass serpentine cavity of the serpentine cavity core, and the squealer pocket core end at the same axial position.

14. The core assembly of claim 13 , further comprising at least one stand-off connecting the dead-end tip flag cavity core to the serpentine cavity core, wherein the at least one stand-off forms bleed hole in the formed airfoil and arranged to fluidly connect the formed dead-end tip flag cavity and the formed serpentine cavity.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Niezelski David A
• Jennings Timothy J
• Teller Bret M
• Mcbrien John
• Slavens Thomas N

Classifications

• F01D25/12

  Cooling · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• Y02T50/60

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