Internally cooled airfoil

Patent metadata

Field	Value
Publication number	US-10508552-B2
Application number	US-201615096243-A
Country	US
Kind code	B2
Filing date	Apr 11, 2016
Priority date	Apr 11, 2016
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

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

First claim

What is claimed is:

1. An airfoil, comprising:
a tip flag cavity comprising a forward pedestal and a first spear pedestal disposed aft of the forward pedestal;
a forward internal cavity configured to provide cooling fluid to the tip flag cavity;
a trailing edge discharge cavity separated from the tip flag cavity and comprising,
a first row of pedestals comprising a first racetrack pedestal,
a second row of pedestals aft of the first row of pedestals, the second row of pedestals comprising a second racetrack pedestal,
a third row of pedestals aft of and spaced apart from the second row of pedestals in an aft direction, the third row of pedestals comprising a circular pedestal, and
a fourth row of pedestals aft of the third row of pedestals, the fourth row of pedestals comprising a second spear pedestal; and

a trailing edge cavity aft of the forward internal cavity and configured to provide the cooling fluid to the trailing edge discharge cavity
wherein the first spear pedestal and the second spear pedestal 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 comprising a greater diameter than the aft circular portion, and
wherein the first racetrack pedestal and the second racetrack pedestal each comprise two parallel surfaces joined on either end by a half circular end.

2. The airfoil of claim 1 , wherein a diameter of the first racetrack pedestal is equal to a diameter of the second racetrack pedestal.

3. The airfoil of claim 2 , wherein a diameter of the first spear pedestal is greater than the diameter of the first racetrack pedestal.

4. The airfoil of claim 1 , wherein a first blockage of the first row of pedestals is 71%, wherein a second blockage of the second row of pedestals is 71%, wherein a third blockage of the third row of pedestals is 51%, and wherein a fourth blockage of the fourth row of pedestals is 51%.

5. The airfoil of claim 1 , wherein a diameter of the forward pedestal is equal to a diameter of the circular pedestal.

6. The airfoil of claim 1 , wherein the first spear pedestal comprises a first depth and the second spear pedestal comprises a second depth less than the first depth.

7. The airfoil of claim 6 , wherein the first depth is 0.020 inches and the second depth is 0.012 inches.

8. An internally cooled engine component, comprising:
a tip flag cavity comprising a forward pedestal and a first spear pedestal disposed aft of the forward pedestal;
a forward internal cavity configured to provide cooling fluid to the tip flag cavity;
a trailing edge discharge cavity separated from the tip flag cavity and comprising,
a first row of pedestals comprising a first racetrack pedestal, wherein a first blockage of the first row of pedestals is 71%,
a second row of pedestals aft of the first row of pedestals, the second row of pedestals comprising a second racetrack pedestal, wherein a second blockage of the second row of pedestals is 71%,
a third row of pedestals aft of and spaced apart from the second row of pedestals in an aft direction, the third row of pedestals comprising a circular pedestal, wherein a third blockage of the third row of pedestals is 51%, and
a fourth row of pedestals aft of the third row of pedestals, the fourth row of pedestals comprising a second spear pedestal, wherein a fourth blockage of the fourth row of pedestals is 51%; and

a trailing edge cavity aft of the forward internal cavity and configured to provide the cooling fluid to the trailing edge discharge cavity
wherein the first spear pedestal and the second spear pedestal 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 comprising a greater diameter than the aft circular portion, and
wherein the first racetrack pedestal and the second racetrack pedestal each comprise two parallel surfaces joined on either end by a half circular end.

Assignees

• United Technologies Corp

Inventors

• Auxier James T
• Jariwala Parth
• Teller Bret M

Classifications

• F05D2230/21

  by casting · CPC title

• F05D2240/127

  Vortex generators, turbulators, or the like, for mixing · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• 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

• F05D2260/202

  by film cooling · CPC title