Gas turbine engine component suction side trailing edge cooling scheme

• US 20070243065A1
• Filed: 04/18/2006
• Published: 10/18/2007
• Est. Priority Date: 04/18/2006
• Status: Active Grant

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Paauwe, Corneil, Devore, Matthew
• Granted Patent: US 7,465,154 B2
• Time in Patent Office: Days
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

A gas turbine engine component has a cooling scheme that utilizes an impingement tube to cool the suction wall and the pressure wall of a mid portion of an airfoil. The impingement tube is formed to not have impingement holes on an end of the impingement tube spaced toward the trailing edge along the suction wall. Impingement holes are formed in the same portion on a side of the impingement tube facing the pressure wall. Pedestals extend from an inner face of the suction wall toward the impingement tube in this area. The use of the pedestals over this area provides greater cooling to a focused area on the suction wall of the airfoil that might otherwise receive inadequate film cooling.

Claims

1. A gas turbine engine component comprising:

a component body extending from a leading edge toward a trailing edge, said component body having an airfoil shape with a pressure side and a suction side;

a cooling channel formed within said component body, and an impingement tube received within said cooling channel, such that cooling fluid may be directed into said impingement tube for passing along a length of said component body and outwardly through impingement holes in said impingement tube, and against an inner wall of both said pressure side and said suction side, said cooling channel having pedestals spaced towards said trailing edge relative to said impingement tube; and

supplemental pedestals formed on said inner wall of said suction side and extending toward said impingement tube at an end of said impingement tube spaced toward said trailing edge.

2. The gas turbine engine component as set forth in claim 1, wherein said impingement tube has no impingement holes in a suction side portion of said impingement tube aligned with said supplemental pedestals.

3. The gas turbine engine component as set forth in claim 1, wherein the size of passages are designed such that a ratio of air flow passing outwardly of a suction side of said impingement tube and reaching exit holes in said trailing edge compared to the air flow passing from said pressure side of said impingement tube and reaching said exit holes in said trailing edge is greater than 5:

1.

4. The gas turbine engine component as set forth in claim 3, wherein a sealing effect assists in resisting air flow passing from said pressure side of said impingement tube and reaching said exit holes.

5. The gas turbine engine component as set forth in claim 4, wherein said resistance is provided by fluid effects.

6. The gas turbine engine component as set forth in claim 1, wherein a second cooling channel is spaced toward said leading edge from said cooling channel, and said second cooling channel also receiving an impingement tube and a film cooling hole being formed in a wall at said suction side to receive air from said second cooling channel.

7. The gas turbine engine component as set forth in claim 1, wherein said supplemental pedestals increase in height in a direction measured from said leading edge toward said trailing edge.

8. The gas turbine engine component as set forth in claim 7, wherein a distance between said inner wall and said impingement tube at said suction side increases as the impingement tube extends from the leading edge toward the trailing edge.

9. The gas turbine engine component as set forth in claim 8, wherein a distance measured between said inner wall and said impingement tube at said pressure side remains relatively constant as the impingement tube extends from the leading edge toward the trailing edge.

10. The gas turbine engine component as set forth in claim 1, wherein said gas turbine engine component is a stationary vane.

11. A turbine engine comprising:

a combustion section;

a turbine section including a turbine rotor rotating about an axis; and

at least one component of the turbine engine having a component body extending from a leading edge toward a trailing edge, said component body having an airfoil shape with a pressure side and a suction side, a cooling channel formed within said component body, and an impingement tube received within said cooling channel, such that cooling fluid may be directed into said impingement tube for passing along a length of said component body and outwardly through impingement holes in said impingement tube, and against an inner wall of both said pressure side and said suction side, said cooling channel having pedestals spaced towards said trailing edge relative to said impingement tube; and

supplemental pedestals formed on said inner wall of said suction side and extending toward said impingement tube at an end of said impingement tube spaced toward said trailing edge.

12. The turbine engine as set forth in claim 11, wherein said impingement tube has no impingement holes in a suction side portion of said impingement tube aligned with said supplemental pedestals.

13. The turbine engine as set forth in claim 11, wherein the size of said passages are designed such that a ratio of air flow passing outwardly of a suction side of said impingement tube and reaching exit holes in said trailing edge compared to the air flow passing from said pressure side of said impingement tube and reaching said exit holes in said trailing edge is 5:

1.

14. The turbine engine as set forth in claim 13, wherein a sealing effect assists in resisting air flow passing from said pressure side of said impingement tube and reaching said exit holes.

15. The turbine engine as set forth in claim 14, wherein said resistance is provided by fluid effects.

16. The turbine engine as set forth in claim 11, wherein a second cooling channel is spaced toward said leading edge from said cooling channel, and said second cooling channel also receiving an impingement tube and a film cooling hole being formed in a wall at said suction side to receive air from said second cooling channel.

17. The turbine engine as set forth in claim 11, wherein said supplemental pedestals increase in height in a direction measured from said leading edge toward said trailing edge.

18. The turbine engine as set forth in claim 17, wherein a distance between said inner wall and said impingement tube at said suction side increases as the impingement tube extends from the leading edge toward the trailing edge.

19. The turbine engine as set forth in claim 18, wherein a distance measured between said inner wall and said impingement tube at said pressure side remains relatively constant as the impingement tube extends from the leading edge toward the trailing edge.

20. The turbine engine as set forth in claim 11, wherein said component is a stationary vane.