Gas turbine engine airfoil with dirt purge feature and core for making same

Patent metadata

Field	Value
Publication number	US-9279331-B2
Application number	US-201213453137-A
Country	US
Kind code	B2
Filing date	Apr 23, 2012
Priority date	Apr 23, 2012
Publication date	Mar 8, 2016
Grant date	Mar 8, 2016

Abstract

An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed.

First claim

What is claimed is:

1. An airfoil comprising:
a body including leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface, first and second cooling passages extending in a radial direction from a root to a tip, the first cooling passage including a tip flag passage radially inboard from the tip and extending in a chord-wise direction to a first end that penetrates the trailing edge, the second cooling passage including a second end terminating adjacent the tip flag passage, and a dirt purge passage interconnecting the second end to the tip flag passage.

2. The airfoil according to claim 1 , comprising a trailing edge passage extending from the second cooling passage that penetrates the trailing edge.

3. The airfoil according to claim 2 , comprising pedestals arranged in the trailing edge passage and interconnecting opposing pressure and suction side walls.

4. The airfoil according to claim 2 , wherein the trailing edge passage has a thickness in the range of 0.008 to 0.020 inch (0.20 to 0.51 mm).

5. The airfoil according to claim 2 , wherein the tip flag passage is discrete from the trailing edge passage.

6. The airfoil according to claim 1 , wherein the dirt purge passage includes a width in the range of 0.017 to 0.045 inch (0.43 to 1.14 mm).

7. The airfoil according to claim 1 , comprising a third cooling passage arranged between the first and second cooling passages in the chord-wise direction, the third cooling passage having a serpentine shape and terminating in a third end near the tip flag passage, and a tie passage interconnecting the third end to the tip flag passage.

8. A core for an airfoil comprising:
first and second core portions extending in a radial direction, the first core portion including a tip flag portion extending in a chord-wise direction and having a first end configured to penetrate an airfoil trailing edge, the second core portion including a second end terminating adjacent the tip flag portion; and
a core tie interconnecting the second end to the tip flag portion and configured to provide a dirt purge passage.

9. The core according to claim 8 , comprising a trailing edge core portion extending from the second core portion and configured to penetrate the airfoil trailing edge.

10. The core according to claim 9 , comprising multiple core portions secured to one another and configured to correspond to multiple cooling passages, the first and second core portions provided by a first core, and the trailing edge core portion provided by a second core secured to the first core.

11. The core according to claim 10 , wherein the first core is ceramic, and the second core is refractory metal core.

12. The core according to claim 11 , wherein the second core portion includes a slot receiving the trailing edge core portion.

13. The core according to claim 9 , wherein the trailing edge core portion includes multiple apertures configured to provide airfoil pedestals.

14. The core according to claim 13 , wherein the trailing edge core portion has a thickness in the range of 0.008 to 0.020 inch (0.20 to 0.51 mm).

15. The core according to claim 8 , wherein the core tie includes a width in the range of 0.017 to 0.045 inch (0.43 to 1.14 mm).

16. The core according to claim 8 , comprising a third core portion arranged between the first and second core portions in the chord-wise direction, the third core portion having a serpentine shape and terminating in a third end near the tip flag portion, and a second core tie interconnecting the third end to the tip flag portion.

17. The core according to claim 16 , comprising an inlet core portion arranged opposite the tip flag portion and interconnecting the first, second and third core portions to one another.

18. The core according to claim 8 , wherein the core tie, the second core portion and the tip flag portion are integral with one another and constructed of the same material.

Assignees

• Levine Jeffrey R
• Beattie Jeffrey S
• United Technologies Corp

Inventors

• Levine Jeffrey R
• Beattie Jeffrey S

Classifications

• B22C9/108

  Installation of cores · CPC title

• F05D2300/13

  Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W · CPC title

• F05D2260/607

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

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title