Turbine blade with dust tolerant cooling system

Patent metadata

Field	Value
Publication number	US-10787932-B2
Application number	US-201816035191-A
Country	US
Kind code	B2
Filing date	Jul 13, 2018
Priority date	Jul 13, 2018
Publication date	Sep 29, 2020
Grant date	Sep 29, 2020

Abstract

A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at a positive angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle, and the at least one rib merges with at least one flow scoop to direct the particles and a portion of the cooling fluid into the inlet.

First claim

What is claimed is:

1. A turbine blade, comprising:
an airfoil that extends from a platform to a tip, and from a leading edge to a trailing edge, the airfoil having a pressure side and an opposite suction side, the tip having a tip region that extends from the leading edge toward the trailing edge, the tip region bounded by a wall that extends from the suction side to the pressure side at a positive angle, with a tip flag channel defined by at least the pressure side, the suction side and the wall, the leading edge having a leading edge cooling circuit that is defined from the platform to the tip flag channel, the leading edge cooling circuit in fluid communication with the tip flag channel to direct cooling fluid received from the platform radially into the tip flag channel, and the pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, each of the at least one tip dust hole having an inlet in fluid communication with the tip flag channel and an outlet in fluid communication with a fluid surrounding the tip of the airfoil to direct particles in the cooling fluid out of the airfoil; and
at least one rib defined on the wall that extends from the suction side to the pressure side at a second angle, and the at least one rib merges with at least one flow scoop to direct the particles and a portion of the cooling fluid into the inlet of each of the at least one tip dust hole,
wherein the at least one rib is defined on the wall to extend into the tip flag channel at a third angle.

2. The turbine blade of claim 1 , wherein the at least one flow scoop is defined on the pressure side about a portion of a perimeter of the inlet of each of the at least one tip dust hole and extends outwardly into the tip flag channel.

3. The turbine blade of claim 1 , wherein each of the at least one rib has a first side that extends into the tip flag channel and a second side coupled to the wall, the first side of each of the at least one rib extends from a first end of the at least one rib to a second end of the at least one rib at the second angle, which is different than the positive angle.

4. The turbine blade of claim 1 , wherein the inlet of each of the at least one tip dust hole is offset from the outlet of each of the at least one tip dust hole such that each of the at least one tip dust hole extends along an arc.

5. The turbine blade of claim 4 , wherein the pressure side of the airfoil includes a squealer tip extension, and the at least one tip dust hole is defined through the squealer tip extension.

6. The turbine blade of claim 1 , wherein the leading edge cooling circuit includes a plurality of cooling features that are spaced apart radially within the leading edge cooling circuit.

7. The turbine blade of claim 6 , wherein the plurality of cooling features comprise a plurality of pins arranged in a plurality of rows, with each pin of the plurality of pins having a first pin end coupled to a first wall opposite the leading edge and a second pin end coupled to a second wall opposite the first wall such that each pin of the plurality of pins spans the leading edge cooling circuit.

8. The turbine blade of claim 1 , wherein the outlet of each of the at least one tip dust hole is defined through the pressure sidewall.

9. The turbine blade of claim 1 , wherein the wall of the tip region is a tip cap, and the outlet of each of the at least one tip dust hole is defined through the tip cap.

10. A turbine blade, comprising:
an airfoil that extends from a platform to a tip, and from a leading edge to a trailing edge, the airfoil having a pressure side and an opposite suction side, the pressure side of the airfoil including a squealer tip extension, the tip having a tip region that extends from the leading edge toward the trailing edge, the tip region bounded by a wall that extends from the suction side to the pressure side at a positive angle, with a tip flag channel defined by at least the pressure side, the suction side and the wall, the leading edge having a leading edge cooling circuit that is defined from the platform to the tip flag channel, the leading edge cooling circuit in fluid communication with the tip flag channel to direct cooling fluid received from the platform radially into the tip flag channel, and the pressure side includes at least one tip dust hole defined through the squealer tip extension, each of the at least one tip dust hole having an inlet in fluid communication with the tip flag channel and an outlet in fluid communication with a fluid surrounding the tip of the airfoil to direct particles in the cooling fluid out of the airfoil, the inlet of each of the at least one tip dust hole is offset from the outlet of each of the at least one tip dust hole; and
at least one rib defined on the wall that extends from the suction side to the pressure side, each of the at least one rib having a first side that extends into the tip flag channel and a second side coupled to the wall, the first side of each of the at least one rib extending from a first end of the at least one rib to a second end of the at least one rib at a second angle, which is different than the positive angle, and the at least one rib merges with at least one flow scoop to direct the particles and a portion of the cooling fluid into the inlet of each of the at least one tip dust hole.

11. The turbine blade of claim 10 , wherein the at least one flow scoop is defined on the pressure side about a portion of a perimeter of the inlet of each of the at least one tip dust hole and extends outwardly into the tip flag channel about the portion of the perimeter of the inlet.

12. The turbine blade of claim 10 , wherein the at least one tip dust hole extends along an arc within the squealer tip extension.

13. The turbine blade of claim 10 , wherein the leading edge cooling circuit includes a plurality of cooling features that are spaced apart radially within the leading edge cooling circuit.

14. The turbine blade of claim 13 , wherein the plurality of cooling features comprise a plurality of pins arranged in a plurality of rows, with each pin of the plurality of pins having a first pin end coupled to a first wall opposite the leading edge and a second pin end coupled to a second wall opposite the first wall such that each pin of the plurality of pins spans the leading edge cooling circuit.

15. A turbine blade, comprising:
an airfoil that extends from a platform to a tip, and from a leading edge to a trailing edge, the airfoil having a pressure side and an opposite suction side, the pressure side of the airfoil including a squealer tip extension, the tip having a tip region that extends from the leading edge toward the trailing edge, the tip region bounded by a wall that extends from the suction side to the pressure side at a positive angle, with a tip flag channel defined by at least the pressure side, the suction side and the wall, the leading edge having a leading edge cooling circuit that is defined from the platform to the tip flag channel, the leading edge cooling circuit in fluid communication with the tip flag channel to direct cooling fluid received from the platform radially into the tip flag channel, and the pressure side includes at least one tip dust hole defined through the squealer tip extension, each of the at least one tip dust hole having an inlet in fluid communication with the tip flag channel and an outlet in fluid communication with a fluid surrounding the tip of the airfoil to direct particles in the cooling fluid out of the airfoil, the inlet of each of the at least one tip dust hole is offset from the outlet of each

Assignees

• Honeywell Int Inc

Inventors

• Crites Daniel C
• Morris Mark C
• Whitaker Steven
• Waldman David

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D25/32 Primary

  Collecting of condensation water; Drainage {; Removing solid particles} · CPC title