Internally cooled airfoil

Patent metadata

Field	Value
Publication number	US-10830054-B2
Application number	US-201916675879-A
Country	US
Kind code	B2
Filing date	Nov 6, 2019
Priority date	Apr 11, 2016
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A casting core may comprise a tip flag material having a forward cavity and a first spear cavity disposed aft of the forward cavity. A trailing edge discharge material may be separated from the tip flag material and include a first row of cavities. The first row of cavities may comprise a first racetrack cavity. A second row of cavities may be disposed aft of the first row of cavities and include a second racetrack cavity. A third row of cavities may be disposed aft of the second row of cavities and include a circular cavity. A fourth row of cavities may be disposed aft of the third row of cavities and include a second spear cavity.

First claim

What is claimed is:

1. A casting core, comprising:
a tip flag material comprising a forward cavity and a first spear cavity disposed aft of the forward cavity; and
a trailing edge discharge material separated from the tip flag material and comprising,
a first row of cavities comprising a first racetrack cavity,
a second row of cavities aft of the first row of cavities, the second row of cavities comprising a second racetrack cavity,

a third row of cavities aft of and spaced apart from the second row of cavities in an aft direction, the third row of cavities comprising a circular cavity, and
a fourth row of cavities aft of the third row of cavities, the fourth row of cavities comprising a second spear cavity, wherein:
the first spear cavity and the second spear cavity each comprise a forward circular portion and an aft circular portion connected by an aft parallel portion and non-parallel surfaces,
the forward circular portion comprises a greater diameter than the aft circular portion, and
the first racetrack cavity and the second racetrack cavity each comprise two parallel surfaces joined on either end by a half circular end.

2. The casting core of claim 1 , wherein a first diameter the half circular end of the first racetrack cavity is equal to a diameter of the half circular end of the second racetrack cavity.

3. The casting core of claim 2 , wherein a third diameter of the first spear cavity is greater than the first diameter of the first racetrack cavity.

4. The casting core of claim 3 , wherein the third diameter of the first spear cavity is 0.026 inches.

5. The casting core of claim 1 , wherein the first row of cavities comprises 12 racetrack cavities, and the fourth row of cavities comprises 24 spear cavities.

6. The casting core of claim 1 , wherein a first diameter of the forward cavity is equal to a second diameter of the circular cavity.

7. The casting core of claim 1 , wherein a first geometry of the first spear cavity is the same as a second geometry of the second spear cavity.

8. The casting core of claim 1 , wherein the first row of cavities is staggered relative to the second row of cavities.

9. The casting core of claim 1 , wherein the first spear cavity comprises a first depth and the second spear cavity comprises a second depth less than the first depth.

10. The casting core of claim 9 , wherein the first depth is 0.020 inches and the second depth is 0.012 inches.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Auxier James T
• Jariwala Parth
• Teller Bret M

Classifications

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2230/21

  by casting · CPC title