Cooled hot section components for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10344611-B2
Application number	US-201615158782-A
Country	US
Kind code	B2
Filing date	May 19, 2016
Priority date	May 19, 2016
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A gas turbine engine includes a turbine section including a plurality of blade outer air seals disposed therein, the blade outer air seals each including a body including a raised material that extends beyond the outer surface of the body and the raised material includes an inlet hole formed through the raised material.

First claim

What is claimed is:

1. A blade outer air seal for a gas turbine engine, comprising:
a body including lateral edges, radial edges, and an outer surface, wherein the lateral edges and the radial edges provide sealing and containing for a rotating turbomachine blade,
the outer surface of the body including a plurality of raised material surfaces that are spaced about the outer surface,
each of the raised material surfaces being arranged in two sets of raised material surfaces, each of the sets of raised material surfaces being disposed adjacent a respective one of the radial edges, each of the sets of raised material surfaces including at least two raised material surfaces that are mutually spaced between the lateral edges,
the plurality of raised material surfaces extending beyond the outer surface of the body, the plurality of raised material surfaces comprising beveled edges and being smaller than the outer surface,
a plurality of holes distributed among the respective plurality of raised material surfaces, so that each of the plurality of raised material surfaces includes one of the plurality of holes,
wherein the plurality of holes are a plurality of raised inlet holes formed through the plurality of raised material surfaces and formed perpendicular to the body so that each of the plurality of holes is raised above the outer surface, and
wherein the plurality of raised surfaces create convoluted air flow paths to be received by the plurality of holes, and
wherein the radial edges include exit holes in fluid communication with the plurality of raised inlet holes.

2. The blade outer air seal of claim 1 , wherein the raised material is prismatoidal.

3. The blade outer air seal of claim 1 , wherein the raised material is cylindrical.

4. The blade outer air seal of claim 1 , wherein the raised material is conical.

5. The blade outer air seal of claim 1 , wherein the raised material is hemispherical.

6. The blade outer air seal of claim 1 , wherein at least one of the inlet holes is cast in the raised material.

7. The blade outer air seal of claim 1 , wherein at least one of the inlet holes is drilled in the raised material.

8. The blade outer air seal of claim 1 , wherein at least one of the inlet holes is electrically machined in the raised material.

9. The blade outer air seal of claim 1 , wherein at least one of the inlet holes is in fluid communication with an exit hole.

10. A gas turbine engine, comprising:
a turbine section including a plurality of blade outer air seals disposed therein, the blade outer air seals each including:
a body including lateral edges, radial edges, and an outer surface, wherein the lateral edges and the radial edges provide sealing and containing for a rotating turbomachine blade,
the outer surface of the body including a plurality of raised material surfaces that are spaced about the outer surface,
each of the raised material surfaces being arranged in one of two sets of raised material surfaces, each of the sets of raised material surfaces being disposed adjacent a respective one of the radial edges, each of the sets of raised material surfaces including at least two raised material surfaces that are mutually spaced between the lateral edges,
the plurality of raised material surfaces extending beyond the outer surface of the body, the plurality of raised material surfaces comprising beveled edges and being smaller than the outer surface,
a plurality of holes distributed among the respective plurality of raised material surfaces, so that each of the plurality of raised material surfaces includes one of the plurality of holes,
wherein the plurality of holes are a plurality of raised inlet holes formed through the plurality of raised material surfaces and formed perpendicular to the body so that each of the plurality of holes is raised above the outer surface, and
wherein the plurality of raised surfaces create convoluted air flow paths to be received by the plurality of holes, and
wherein the radial edges include exit holes in fluid communication with the plurality of raised inlet holes.

11. The gas turbine engine of claim 10 , wherein the raised material is prismatoidal.

12. The gas turbine engine of claim 10 , wherein the raised material is cylindrical.

13. The gas turbine engine of claim 10 , wherein the raised material is conical.

14. The gas turbine engine of claim 10 , wherein the raised material is hemispherical.

15. The gas turbine engine of claim 10 , wherein at least one of the inlet holes is cast in the raised material.

16. A method to prevent obstruction of an inlet hole via particles, the method comprising:
providing an airflow to a blade outer air seal and
directing the airflow in a convoluted path to divert the particles via the blade outer air seal, the blade outer air seal including:
a body including lateral edges, radial edges, and an outer surface, wherein the lateral edges and the radial edges provide sealing and containment for a rotating turbomachine blade,
the outer surface of the body including a plurality of raised material surfaces that are spaced about the outer surface,
each of the raised material surfaces being arranged in one of two sets of raised material surfaces, each of the sets of raised material surfaces being disposed adjacent a respective one of the radial edges, each of the sets of raised material surfaces including at least two raised material surfaces that are mutually spaced between the lateral edges,
the plurality of raised material surfaces extending beyond the outer surface of the body, the plurality of raised material surfaces comprising beveled edges and being smaller than the outer surface,
a plurality of holes distributed among the respective plurality of raised material surfaces, so that each of the plurality of raised material surfaces includes one of the plurality of holes,
wherein the plurality of holes are a plurality of raised inlet holes formed through the plurality of raised material surfaces and formed perpendicular to the body so that each of the plurality of holes is raised above the outer surface, and
wherein the plurality of raised surfaces create convoluted air flow paths to be received by the plurality of holes, and
wherein the radial edges include exit holes in fluid communication with the plurality of raised inlet holes.

Assignees

• United Technologies Corp

Inventors

• Galle Nathan K

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• F05D2250/232

  conical · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title