Low turn loss baffle flow diverter

Patent metadata

Field	Value
Publication number	US-10012092-B2
Application number	US-201514824195-A
Country	US
Kind code	B2
Filing date	Aug 12, 2015
Priority date	Aug 12, 2015
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow. The internal passage includes first and second passage sections coupled at a turn section. A baffle includes a body arranged in the second passage section to define two cooling flow paths, and a first wedge region extends from the body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the two cooling flow paths.

First claim

What is claimed is:

1. An airfoil, comprising:
an airfoil body having an internal passage for conveying a fluid flow, the internal passage including first and second passage sections coupled at a turn section; and
a baffle including an elongated body arranged in the second passage section to define two cooling flow paths, and a first wedge region extending from the elongated body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the two cooling flow paths;
wherein the first wedge region includes first and second sloped sides having respective surfaces sloping inwardly from opposed walls of the elongated body and joined at an apex; and
wherein the baffle includes a second wedge region having surfaces sloping inwardly from the first wedge region towards the elongated body.

2. The airfoil as recited in claim 1 , wherein the apex of the first wedge region is oriented in a direction towards an outer wall of the turn section.

3. The airfoil as recited in claim 2 , wherein the apex is arranged such that a division of the fluid flow into the two cooling flow paths at the apex is within a predetermined range.

4. The airfoil as recited in claim 2 , wherein the baffle is arranged in the internal passage such that a ratio of a volume of one of the two cooling flow paths and a volume of another one of the cooling flow paths in the turn section is within a predetermined range.

5. The airfoil as recited in claim 1 , wherein the first sloped side defining a first reference plane intersecting surfaces of the turn section to define a first angle, the first angle being equal to or less than 45 degrees.

6. The airfoil as recited in claim 1 , wherein the elongated body defines a hollow interior, and the baffle defines one or more openings configured to communicate coolant flow between the hollow interior and the internal passage.

7. The airfoil as recited in claim 1 , wherein a cross-section of the baffle taken transverse to a longitudinal direction of the baffle at the turn section has five to seven distinct sides.

8. The airfoil as recited in claim 1 , wherein the second wedge region is spaced from outer surfaces of the turn section.

9. The airfoil as recited in claim 8 , wherein the second wedge region abuts a terminal end of a rib separating the first and second passage sections, the rib defining a notch configured to receive a portion of the second wedge region such that the portion of the second wedge region is radially inboard of a radially outermost portion of the terminal end of the rib.

10. The airfoil as recited in claim 1 , wherein one of the two cooling flow paths is bounded by a pressure side of the airfoil body, and another one of the two cooling flow paths is bounded by a suction side of the airfoil body.

11. The airfoil as recited in claim 1 , wherein the airfoil body extends from a platform section, and the platform section defines a cavity configured to at least partially receive the baffle.

12. A baffle for an airfoil, comprising:
an elongated body configured to be received in an internal passage of an airfoil;
a first wedge region including surfaces sloping inwardly from opposed walls of the elongated body and joined at an apex; and
a second wedge region including surfaces sloping inwardly from the first wedge towards the elongated body.

13. The baffle as recited in claim 12 , wherein the apex is offset towards one of the opposed walls.

14. The baffle as recited in claim 12 , wherein a cross-section of the baffle taken at one of the first wedge region and the second wedge region has five to seven distinct sides.

15. A gas turbine engine, comprising:
a rotor spaced axially from a vane; and
wherein at least one of the rotor and the vane includes an airfoil body, the airfoil body comprising:
an internal passage for conveying a fluid flow, the internal passage including first and second passage sections coupled at a turn section;
a baffle including an elongated body arranged in the second passage section to define at least two cooling flow paths, and a first wedge region extending from the elongated body into the first passage section such that the second passage section branches between the at least two cooling flow paths at a location adjacent to the turn section;
wherein the first wedge region includes first and second sloped sides having respective surfaces sloping inwardly from opposed walls of the elongated body and joined at an apex; and
wherein the baffle includes a second wedge region having surfaces sloping inwardly from the first wedge region towards the elongated body.

16. The gas turbine engine as recited in claim 15 , wherein the apex is arranged in the turn section such that a division of the fluid flow into each of the at least two cooling paths at the apex is within a predetermined range.

17. The gas turbine engine as recited in claim 16 , wherein the apex slopes towards a rib of the airfoil body separating the first and second passage sections.

18. The gas turbine engine as recited in claim 16 , wherein the airfoil body extends from a platform section, and an end portion of the baffle extends through the platform section.

19. The gas turbine engine as recited in claim 15 , wherein the second wedge region extends from the elongated body into the first passage section, and the second wedge region is spaced apart from outer surfaces of the turn section.

20. The gas turbine engine as recited in claim 15 , wherein the internal passage is a serpentine passage.

21. The airfoil as recited in claim 9 , wherein:
the elongated body abuts the rib;
each of the two cooling flow paths extend along a length of opposed ends of the baffle and are bounded by walls of the rib; and
the second wedge region is spaced from outer surfaces of the turn section.

22. The gas turbine engine as recited in claim 17 , wherein the elongated body defines a hollow interior, the baffle defines one or more openings configured to communicate coolant flow between the hollow interior and the at least two cooling flow paths, one of the at least two cooling flow paths is bounded by a pressure side of the airfoil body, and another one of the at least two cooling flow paths is bounded by a suction side of the airfoil body.

23. The gas turbine engine as recited in claim 22 , wherein the airfoil body extends from a platform section, the rib separates the first and second passage sections and bounds the turn section, and the elongated body is arranged in the second passage section to abut the rib such that each of the at least two cooling flow paths extend along the length of opposed ends of the baffle and are bounded by walls of the rib.

Assignees

• United Technologies Corp

Inventors

• Mongillo Dominic J
• Spangler Brandon W

Classifications

• F01D5/189

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title