Hourglass airfoil cooling configuration

Patent metadata

Field	Value
Publication number	US-11624322-B2
Application number	US-202117392573-A
Country	US
Kind code	B2
Filing date	Aug 3, 2021
Priority date	Jul 18, 2019
Publication date	Apr 11, 2023
Grant date	Apr 11, 2023

Abstract

A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first passage core. The first passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

First claim

The invention claimed is:

1. A method of manufacturing a core structure for casting an airfoil, comprising:
providing a core die having a first block and a second block, and a plurality of ribs extending from the first block and the second block;
casting an airfoil core in the core die about the plurality of ribs, the plurality of ribs arranged to form a first, second, and third cooling passage core, the first and third cooling passage cores having an hourglass shape and the second cooling passage core arranged between the first and third cooling passage cores and having a kite shape, wherein a perimeter of the second cooling passage core includes an opposed pair of acute angles and an opposed pair of obtuse angles that establish the kite shape; and
separating the first block and the second block to release the airfoil core from the core die.

2. The method of claim 1 , wherein the first and second blocks each have a plurality of pockets aligned with the ribs.

3. The method of claim 2 , comprising sliding the ribs into the pockets before separating the first and second blocks.

4. The method of claim 3 , wherein:
the step of sliding the ribs into the pockets occurs subsequent to the step of casting the airfoil core in the core die, but prior to the step of separating the first and second blocks.

5. The method of claim 1 , wherein at least one of the plurality of ribs extends from the first block in a first direction, and at least one of the plurality of ribs extends from the second block in a second direction.

6. The method of claim 5 , wherein the separating step comprises moving the first block in a direction opposite the first direction and moving the second block in a direction opposite the second direction.

7. The method of claim 1 , wherein the plurality of ribs are formed from a sacrificial material that is configured to melt out of the airfoil core.

8. The method of claim 1 , wherein the first and second blocks are formed from a metallic material.

9. The method of claim 1 , wherein the airfoil core is formed from a ceramic material.

10. The method of claim 1 , wherein:
the plurality of ribs includes a first set of ribs and a second set of ribs; and
the step of providing the core die occurs such that the first set of ribs extend outwardly from the first block towards the second block and such that the second set of ribs extend outwardly from the second block towards the first block to abut a respective rib of the first set of ribs prior to the casting step.

11. The method of claim 9 , wherein:
the first set of ribs and the second set of ribs establish a first core cavity, a second core cavity and a third core cavity;
the forming step includes forming the first cooling passage core in the first core cavity, forming the second cooling passage core in the second core cavity, and forming the third cooling passage core in the third core cavity;
a minimum width of the first core cavity is established at a position in which the first set of ribs abut the second set of ribs;
a minimum width of the third core cavity is established at a position in which the first set of ribs abut the second set of ribs; and
a maximum width of the second core cavity is established at a position in which the first set of ribs abut the second set of ribs.

12. The method of claim 1 , wherein:
the step of providing the core die occurs such that the first set of ribs are spaced apart from the second block and such that the second set of ribs are spaced apart from the first block.

13. The method of claim 12 , wherein:
the first block includes a first set of pockets in a thickness of the first block, the first set of pockets aligned with respective ribs of the first set of ribs; and
the second block includes a second set of pockets in a thickness of the second block, the second set of pockets aligned with respective ribs of the second set of ribs.

14. The method of claim 13 , comprising:
sliding the first set of ribs into the respective pockets of the first set of pockets subsequent to the step of casting the airfoil core in the core die, but prior to the step of separating the first and second blocks; and
sliding the second set of ribs into the respective pockets of the second set of pockets subsequent to the step of casting the airfoil core in the core die, but prior to the step of separating the first and second blocks.

15. The method of claim 14 , wherein:
the first cooling passage core and the second passage core are established on opposite sides of one of the ribs of the first set of ribs and on opposite sides of one of the ribs of the second sets of ribs that abuts the one of the ribs of the first set of ribs; and
the second passage core and the third passage core are established on opposite sides of another one of the ribs of the first set of ribs and on opposite sides of another one of the ribs of the second sets of ribs that abuts the another one of the ribs of the first set of ribs.

Assignees

• Raytheon Tech Corp

Inventors

• Spangler Brandon W

Classifications

• B22C9/10

  Cores; Manufacture or installation of cores {(breaker cores B22C9/084)} · CPC title

• Y02T50/60

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

• B22C9/103

  Multipart cores · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/204

  by the use of microcircuits · CPC title