Trailing edge cooling pedestal configuration for a gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-2016333699-A1
Application number	US-201415110904-A
Country	US
Kind code	A1
Filing date	Dec 26, 2014
Priority date	Jan 30, 2014
Publication date	Nov 17, 2016
Grant date	—

Abstract

An airfoil for a gas turbine engine includes pressure and suction surfaces that are provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extending to the trailing edge. The cooling passage terminates in a trailing edge exit that is arranged in the trailing edge. Multiple rows of pedestals include a first row of pedestals that join the pressure and suction walls. The first row of pedestals is arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.

First claim

What is claimed is:

1 . An airfoil for a gas turbine engine comprising:
pressure and suction surfaces provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge; a cooling passage arranged between the pressure and suction walls and extending to the trailing edge, the cooling passage terminating in a trailing edge exit arranged in the trailing edge; and multiple rows of pedestals include a first row of pedestals joining the pressure and suction walls, the first row of pedestals arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.

2 . The airfoil according to claim 1 , comprising first, second, and third rows of pedestals each extending in a radial direction and spaced from one another in a chord-wise direction.

3 . The airfoil according to claim 2 , wherein at least one the first, second and third rows of pedestals include first, second, third and fourth groups of pedestal, at least one group having pedestals that are different sizes than the pedestals of another group.

4 . The airfoil according to claim 3 , wherein one of the rows of pedestals includes four groups of pedestals, the first group is arranged near an airfoil tip, and the fourth group arranged near a platform from which the airfoil extends, pedestals in the first and third group being the same size.

5 . The airfoil according to claim 4 , wherein pedestals in the fourth group are larger than the pedestals in the first and third groups.

6 . The airfoil according to claim 4 , wherein pedestals in the second group are smaller than the pedestals in the first and third groups.

7 . The airfoil according to claim 3 , wherein pedestals in at least one of the groups are round, and pedestal in at least another of the groups is oblong.

8 . The airfoil according to claim 7 , wherein the oblong pedestals have a radius at opposing ends of about 0.020 inch (0.51 mm) and are about 0.050-0.060 inch (1.27-1.52 mm) long.

9 . The airfoil according to claim 7 , wherein the round pedestals have a radius of about 0.020-0.030 inch (0.51-0.76 mm)

10 . The airfoil according to claim 1 , wherein the pedestals are spaced apart from one another within a row by about 0.042-0.063 inch (1.07-1.60 mm) between centerlines of adjacent pedestals.

11 . The airfoil according to claim 2 , wherein a trailing edge exit has an uncoated width in a thickness direction, which is perpendicular to the chord-wise direction, of about 0.020 inch (0.51 mm)

12 . The airfoil according to claim 2 , wherein the first and second rows are separated by about 0.100-0.140 inch (2.54-3.56 mm) between centerlines of adjacent pedestals in the chord-wise direction.

13 . The airfoil according to claim 2 , wherein the second and third rows are separated by about 0.110-0.150 inch (2.79-3.81 mm) between centerlines of adjacent pedestals in the chord-wise direction.

14 . The airfoil according to claim 2 , wherein the third row and the trailing edge are separated by about 0.495-0.535 inch (12.57-13.59 mm) between a centerline of the third row pedestals and the trailing edge in the chord-wise direction.

15 . The airfoil according to claim 1 , wherein the pressure and suction surfaces support a thermal barrier coating.

16 . The airfoil according to claim 15 , comprising a thermal barrier coating in the trailing edge exit without reaching the first row of pedestals.

17 . The airfoil according to claim 1 , wherein the airfoil is a turbine blade.

18 . The airfoil according to claim 1 , wherein the cooling passage at the trailing edge has a generally uniform width.

19 . The airfoil according to claim 2 , wherein at least one the first, second and third rows of pedestals include different groups of pedestals radially spaced from one another, radially outer groups of pedestals arranged nearest an airfoil tip and an airfoil platform are larger than groups of pedestals radially between the radially outer groups of pedestals.

Assignees

• United Technologies Corp

Inventors

• Downey Jr James B
• Zhang Brenda
• Lemieux Steven G
• Kaufman Eleanor D
• Fukuda Takao
• Nadeau Daniel C

Classifications

• F01D25/12

  Cooling · 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

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/2212

  by creating turbulence · CPC title