Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations

Patent metadata

Field	Value
Publication number	US-9650900-B2
Application number	US-201213465647-A
Country	US
Kind code	B2
Filing date	May 7, 2012
Priority date	May 7, 2012
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.

First claim

What is claimed is:

1. An engine component, comprising:
a body with an inner surface and an outer surface; and
a plurality of cooling holes formed in the body, the plurality of cooling holes including a first cooling hole,
wherein the first cooling hole is defined by a single cylindrical upstream portion with a single inlet on the inner surface that transitions into a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe on the outer surface, wherein the first lobe has a first length on the outer surface, the second lobe has a second length on the outer surface, and the third lobe has a third length on the outer surface, and wherein the first length is different than the second length,
wherein the multi-lobe shape is formed by at least a first oval, a second oval, and a third oval, each oval having a first end and a second end, and wherein the first ends of the at least the first oval, the second oval, and the third oval at least partially overlap,
wherein each of the first, second, and third lobes have straight sides such that at least a portion of each of the first, second, and third lobes have a constant width.

2. The engine component of claim 1 , wherein the second ends of the first oval, the second oval, and the third ovals are splayed relative to one another.

3. The engine component of claim 1 , wherein the first oval is extends relative to a first side of the second oval at a first angle, and the third oval extends relative to a second side of the second oval at a second angle.

4. The engine component of claim 3 , wherein the first angle is equal to the second angle.

5. The engine component of claim 3 , wherein the first length and the third length are approximately equal.

6. The engine component of claim 5 , wherein the third length is different than the first length and the second length.

7. The engine component of claim 5 , wherein the second length is less than the first length.

8. The engine component of claim 1 , wherein the multi-lobed shape is arranged in the body relative to mainstream gas flow such that the first ends are upstream and the first, second, and third lobes extend from the from the first ends in a downstream direction.

9. The engine component of claim 8 , wherein the multi-lobed shape is further formed by a fourth oval with a first end at least partially overlapping with the first ends of the first, second, and third ovals.

10. The engine component of claim 1 , wherein the body is an airfoil body.

11. The engine component of claim 1 , wherein the first cooling hole transitions between the single cylindrical upstream portion into the multi-lobed shape approximately half an axial distance between the singe inlet and the outer surface.

12. The engine component of claim 1 , wherein the body is formed from a single crystal material.

13. The engine component of claim 1 , wherein the body is formed from a nickel based alloy.

14. The engine component of claim 1 , wherein areas between the first and second lobes and between the second and third lobes are lands that extend to the exterior surface.

15. A turbine section of a gas turbine engine, comprising:
a housing defining a hot gas flow path;
a plurality of circumferential rows of airfoils disposed in the hot gas flow path, each airfoil defining an inner surface and an outer surface;
a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils, wherein a first cooling hole of the plurality of cooling holes is defined by a single cylindrical upstream portion with a single inlet on the inner surface that transitions into a multi-lobed shape,
wherein the multi-lobe shape is formed by at least a first oval, a second oval, and a third oval, each oval having a first end and a second end, wherein the first ends of the first oval, the second oval, and the third oval at least partially overlap with one another, and wherein the second ends of the first oval, the second oval, and the third ovals are splayed relative to one another with the second oval being in between the first and third ovals such that the first and second ovals are splayed at a first angle and the second and third ovals are splayed at a second angle, wherein the first and second angles are different from one another,
wherein each of the first, second, and third lobes have straight sides such that at least a portion of each of the first, second, and third lobes have a constant width.

16. The turbine section of claim 15 , wherein each of the first oval, the second oval, and the third oval has a different length on the outer surface.

17. An engine component, comprising:
a body with an inner surface and an outer surface; and
a plurality of cooling holes formed in the body, the plurality of cooling holes including a first cooling hole,
wherein the first cooling hole is defined by a single cylindrical upstream portion with a single inlet on the inner surface that transitions into a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe on the outer surface, wherein the first lobe has a first length on the outer surface, the second lobe has a second length on the outer surface, and the third lobe has a third length on the outer surface, and wherein the first length is different than the second length,
wherein the multi-lobe shape is formed by at least a first oval, a second oval, and a third oval, each oval having a first end and a second end, and wherein the first ends of the at least the first oval, the second oval, and the third oval at least partially overlap,
wherein the first, second, and third lobes are each defined by two semicircular ends joined by parallel side portions separated by a respective width, and wherein each of the widths of first, second, and third lobe is different.

Assignees

• Malak Malak Fouad
• Rana Rajiv
• Tapia Luis
• Chou David
• Liu Jong
• Honeywell Int Inc

Inventors

• Malak Malak Fouad
• Rana Rajiv
• Tapia Luis
• Chou David
• Liu Jong

Classifications

• F05D2260/221

  Improvement of heat transfer · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2250/182

  crenellated, notched · CPC title

• F05D2250/14

  elliptical · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic