Cooling arrangement for gas turbine engine components

Patent metadata

Field	Value
Publication number	US-11168570-B1
Application number	US-202017004662-A
Country	US
Kind code	B1
Filing date	Aug 27, 2020
Priority date	Aug 27, 2020
Publication date	Nov 9, 2021
Grant date	Nov 9, 2021

Abstract

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, at least one of an airfoil section and a platform section including a wall. The wall includes a plurality of pedestals having adjacent pedestals extending from an external wall surface to establish a respective cooling passage, and the cooling passage includes an inlet and an outlet. The adjacent pedestals are dimensioned such that the adjacent pedestals taper inwardly from the inlet in a first direction towards the outlet to establish a throat in the respective cooling passage. A method of fabricating a gas turbine engine component is also disclosed.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine comprising:
an airfoil section extending in a radial direction from a platform section, extending in a chordwise direction between a leading edge and a trailing edge, and extending in a thickness direction between a pressure side and a suction side that join together at the leading and trailing edges;
wherein at least one of the airfoil section and the platform section include a wall, the wall extending between an internal wall surface and an external wall surface, and the internal wall surface bounding an internal cavity;
wherein the wall includes a plurality of pedestals having adjacent pedestals extending from the external wall surface to establish a respective cooling passage, and the cooling passage includes an inlet and an outlet, the inlet coupled to the internal cavity along the internal wall surface, and the outlet along the external wall surface;
wherein the adjacent pedestals are dimensioned such that the adjacent pedestals taper inwardly from the inlet in a first direction towards the outlet to establish a throat in the respective cooling passage, and the respective passage expands outwardly from the throat in the first direction towards the outlet to establish a diffusion section interconnecting the throat and the outlet; and
one or more coatings along the external wall surface and into the outlet to establish a coated outlet region of the cooling passage, wherein a minimum cross-sectional area of the cooling passage along the coated outlet region divided by a cross-sectional area of the throat establishes a coated area ratio, and the coated area ratio is greater than or equal to 0.8.

2. The airfoil as recited in claim 1 , wherein each of the adjacent pedestals comprises a ceramic or metallic material, and the one or more coatings comprise a ceramic and/or a metallic material.

3. The airfoil as recited in claim 1 , wherein the outlet is established adjacent to the trailing edge.

4. The airfoil as recited in claim 3 , wherein no other pedestals are situated between facing walls of the adjacent pedestals bounding the cooling passage at the throat.

5. The airfoil as recited in claim 1 , wherein facing walls of the adjacent pedestals are substantially parallel along a first length of the cooling passage between the throat and the diffusion section and are substantially parallel along a second length of the cooling passage between the diffusion section and the outlet.

6. The airfoil as recited in claim 5 , wherein the coated area ratio is less than or equal to 1.3.

7. The airfoil as recited in claim 5 , wherein each of the adjacent pedestals extends along a respective longitudinal axis, the longitudinal axes of the adjacent pedestals establish a pitch, the adjacent pedestals establish a first width across the throat, and wherein a ratio of the first width to the pitch is greater than or equal to 0.25 and is less than or equal to 0.65.

8. The airfoil as recited in claim 5 , wherein:
each of the adjacent pedestals extends along a respective longitudinal axis and along a respective reference plane bisecting the adjacent pedestals along the respective longitudinal axis;
a first cross-sectional area is established along the external wall surface at the outlet of the respective cooling passage, and the first cross-sectional area defined between the reference planes of the adjacent pedestals and between opposed faces bounding the respective cooling passage spanning between facing walls of the adjacent pedestals; and
one minus a ratio of a cross-sectional area of the coated outlet region along the outlet of the respective cooling passage divided by the first cross-sectional area defines a blockage ratio, and the blockage ratio is greater than or equal to 0.35.

9. The airfoil as recited in claim 8 , wherein the coated area ratio is greater than or equal to 0.9 and less than or equal to 1.15.

10. The airfoil as recited in claim 1 , wherein:
opposed faces of the wall extend between the adjacent pedestals to bound the cooling passage, and the opposed faces establishing a first height at the outlet;
a ratio of an average thickness of the one or more coatings along the opposed faces at the outlet divided by the first height is less than or equal to 0.20.

11. The airfoil as recited in claim 1 , wherein the facing walls of the adjacent pedestals are filleted along at least a portion of the cooling passage between the inlet and outlet.

12. A gas turbine engine comprising:
an array of blades and an array of vanes spaced axially from the array of blades in a gas path, the array of blades are rotatable in the gas path, and an array of blade outer air seals (BOAS) arranged about the array of blades to bound the gas path; and
wherein at least one of the array of blades, the array of vanes and the array of BOAS comprises:
an external wall between an internal wall surface and an external wall surface, the internal wall surface bounding an internal cavity;
wherein a plurality of pedestals are established in a thickness of the external wall, the plurality of pedestals including pairs of adjacent pedestals extending from the external wall surface to establish respective cooling passages, and each of the cooling passages includes an inlet and an outlet, the inlet coupled to the internal cavity along the internal wall surface, and the outlet along the external wall surface;
wherein the adjacent pedestals are dimensioned such that the respective cooling passage establishes a throat and a diffusion section interconnecting the throat and the outlet; and
one or more coatings along the external wall surface and into the outlet to establish a coated outlet region of the respective cooling passage, wherein a minimum cross-sectional area of the respective cooling passage along the coated outlet region divided by a cross-sectional area of the throat establishes a coated area ratio, and the coated area ratio is greater than or equal to 0.8.

13. The gas turbine engine as recited in claim 12 , wherein the one or more coatings comprise a ceramic and/or metallic material.

14. The gas turbine engine as recited in claim 12 , wherein an airfoil section comprises the external wall, the airfoil section extending in a thickness direction between pressure and suction sides and extending in a chordwise direction between leading and trailing edges, the outlet is established along the trailing edge.

15. The gas turbine engine as recited in claim 12 , wherein:
the adjacent pedestals are dimensioned such that the respective cooling passage tapers inwardly from the inlet towards the outlet to establish the throat;
facing walls of the adjacent pedestals are substantially parallel along a first length of the respective cooling passage between the throat and the diffusion section and are substantially parallel along the coated outlet region; and
the coated area ratio is less than or equal to 1.3.

16. The gas turbine engine as recited in claim 15 , wherein:
no other pedestals are situated between the facing walls of the adjacent pedestals bounding the cooling passage at the throat; and
each of the adjacent pedestals extends along a respective longitudinal axis, the longitudinal axes of the adjacent pedestals establish a pitch, the adjacent pedestals establish a first width across the throat, and wherein a ratio of the first width to the pitch is greater than or equal to 0.25 and is less than or equal to 0.65.

17. A method of fabricating a gas turbine engine component comprising:
establishing an internal cooling cavity bounded by an external wall;
es

Assignees

• Raytheon Tech Corp

Inventors

• Lewis Scott D

Classifications

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D5/286

  Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion (F01D5/288 takes precedence) · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• Y02T50/60

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

• F05D2260/201

  by impingement of a fluid · CPC title