Impingement baffle for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11525401-B2
Application number	US-202117145843-A
Country	US
Kind code	B2
Filing date	Jan 11, 2021
Priority date	Jan 11, 2021
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

An impingement baffle for directing a cooling fluid onto a target surface includes a baffle body having a first end opposite a second end, and a first side opposite a second side. The second side is spaced a distance apart from the target surface, with the distance varying from the first end to the second end. The baffle body defines impingement holes that extend through the baffle body from the first side to the second side. The impingement holes are spaced apart along the baffle body to receive the cooling fluid. The impingement baffle includes tubular extensions coupled to the second side. Each tubular extension is in fluid communication with a respective one of the impingement holes to direct the cooling fluid onto the target surface. Each tubular extension extends for a length from the second side, and the length of each tubular extension is based on the distance.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a shroud having a first shroud end opposite a second shroud end and defining a target surface between the first shroud end and the second shroud end, the second shroud end including at least one fluid exit;
an impingement baffle for directing a cooling fluid onto the target surface, the impingement baffle including:
a baffle body having a first end opposite a second end, and a first side opposite a second side, the first end coupled to the first shroud end and the second end coupled to the second shroud end, the second side spaced a distance apart from the target surface, with the distance increasing between the second side and the target surface from proximate the first end to the second end to direct the cooling fluid through the at least one fluid exit, the baffle body defining a plurality of impingement holes that extend through the baffle body from the first side to the second side, the plurality of impingement holes spaced apart along the baffle body from the first end to the second end with each of the plurality of impingement holes configured to receive the cooling fluid; and
a plurality of tubular extensions coupled to the second side of the baffle body, each tubular extension of the plurality of tubular extensions in fluid communication with a respective one of the plurality of impingement holes to direct the cooling fluid from the respective one of the plurality of impingement holes onto the target surface, with each tubular extension of the plurality of tubular extensions extending for a length from the second side, and the length of each tubular extension of the plurality of tubular extensions is based on the distance.

2. The gas turbine engine of claim 1 , wherein a density of the plurality of impingement holes and the plurality of tubular extensions increases from the first end toward the second end.

3. The gas turbine engine of claim 1 , wherein the length associated with each tubular extension of the plurality of tubular extensions increases from the first end to the second end.

4. The gas turbine engine of claim 1 , wherein a second distance is defined between a terminal end of each tubular extension of the plurality of tubular extensions and the target surface, and the second distance is the same for each tubular extension of the plurality of tubular extensions.

5. The gas turbine engine of claim 1 , wherein at least one of the plurality of impingement holes has an inlet configured to be in fluid communication with a source of the cooling fluid and an outlet spaced apart from the target surface and defined by a terminal end of a respective one of the plurality of tubular extensions, and the inlet includes a rounded entrance.

6. The gas turbine engine of claim 5 , wherein the respective one of the plurality of tubular extensions converges from the inlet to the terminal end.

7. The gas turbine engine of claim 5 , wherein the respective one of the plurality of tubular extensions is cylindrical.

8. The gas turbine engine of claim 1 , wherein at least one of the plurality of impingement holes has an inlet configured to be in fluid communication with a source of the cooling fluid and an outlet spaced apart from the target surface and defined by a terminal end of a respective one of the plurality of tubular extensions, and the inlet includes a sharp corner.

9. The gas turbine engine of claim 8 , wherein the respective one of the plurality of tubular extensions converges from the inlet to the terminal end.

10. The gas turbine engine of claim 8 , wherein the respective one of the plurality of tubular extensions is cylindrical.

11. The gas turbine engine of claim 1 , wherein the baffle body includes a planar portion proximate the first end and an angled portion defined between the planar portion and the second end, the plurality of impingement holes includes a plurality of first impingement holes associated with the planar portion and a plurality of second impingement holes associated with the angled portion, and the distance between the second side and the target surface along the planar portion is the same.

12. The gas turbine engine of claim 11 , wherein the distance between the second side and the target surface along the angled portion increases from the planar portion to the second end.

13. The gas turbine engine of claim 11 , wherein the plurality of tubular extensions are coupled to the plurality of second impingement holes.

14. The gas turbine engine of claim 13 , wherein the plurality of second impingement holes and the plurality of tubular extensions are non-uniformly spaced about a perimeter of the baffle body along the angled portion.

15. The gas turbine engine of claim 13 , wherein at least one of the plurality of second impingement holes and a respective one of the plurality of tubular extensions is radially aligned with an adjacent one of the plurality of second impingement holes and a respective adjacent one of the plurality of tubular extensions, and at least a second one of the plurality of second impingement holes and a respective second one of the plurality of tubular extensions is radially misaligned with a second adjacent one of the plurality of second impingement holes and a respective second adjacent one of the plurality of tubular extensions.

16. The gas turbine engine of claim 1 , wherein the shroud is associated with a radial turbine of a gas turbine engine, and the shroud is positioned adjacent to a turbine blade of the radial turbine and is configured to receive combustion gases from a turbine nozzle associated with the gas turbine engine.

17. A gas turbine engine, comprising:
a radial turbine having a turbine blade configured to receive combustion gases from a turbine nozzle;
a shroud having a first shroud end opposite a second shroud end and defining a target surface between the first shroud end and the second shroud end, the second shroud end including at least one fluid exit, the shroud positioned adjacent to the turbine blade and configured to receive the combustion gases, the shroud downstream from the turbine nozzle;
an impingement baffle for directing a cooling fluid onto the target surface, the impingement baffle including:
a baffle body having a first end opposite a second end, a first side opposite a second side, the first end coupled to the first shroud end and the second end coupled to the second shroud end, a planar portion that extends from proximate the first end to an angled portion that extends from the planar portion to the second end, the second side along the angled portion spaced a distance apart from the target surface that increases from the planar portion to the second end to direct the cooling fluid through the at least one fluid exit, the baffle body defining a plurality of impingement holes that extend through the baffle body from the first side to the second side, the plurality of impingement holes spaced apart along the baffle body from the first end to the second end with each of the plurality of impingement holes configured to receive the cooling fluid; and
a plurality of tubular extensions coupled to the second side of the baffle body along the angled portion, each tubular extension of the plurality of tubular extensions in fluid communication with a respective one of the plurality of impingement holes defined in the angled portion to direct the cooling fluid from the respective one of the plurality of impingement holes onto the target surface, with each tubular extension of the plurality of tubular extensions extending for a length from the second side such tha

Assignees

• Honeywell Int Inc

Inventors

• Morris Mark
• Petersen Blake
• Smoke Jason

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/046 Primary

  Heating, heat insulation or cooling means · CPC title

• F01D25/12

  Cooling · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title