Effusion cooled transition duct

• US 6,568,187 B1
• Filed: 12/10/2001
• Issued: 05/27/2003
• Est. Priority Date: 12/10/2001
• Status: Expired due to Term

• Current Assignee: H2 IP UK Limited
• Original Assignee: Power Systems Mfg. LLC (Hanwha Corporation)
• Inventors: Jorgensen, Stephen W., Leahy, James H. Jr.
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US09/683,290
• Publication Number:
  US 20030106317A1
• Time in Patent Office: 533 Days
• Field of Search: 607/52, 607/53, 607/54, 607/55, 607/56, 607/57, 607/58, 607/59, 607/60, 60/393.7, 607/98, 608/00
• US Class Current: 60/752
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes

Abstract

An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet sleeve, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. Effusion cooling geometry, including coverage area, hole size, and surface angle will be optimized in the transition duct to tailor the temperature levels and gradients in order to minimize thermally induced stresses. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life.

Claims

1. An effusion cooled transition duct for transferring hot gases from a combustor to a turbine comprising:

a panel assembly comprising;

a first panel formed from a single sheet of metal;

a second panel formed from a single sheet of metal;

said first panel fixed to said second panel by a means such as welding thereby forming a duct having an inner wall, an outer wall, a thickness therebetween said walls, a generally cylindrical inlet end, and a generally rectangular exit end, said inlet end defining a first plane, said exit end defining a second plane, said first plane oriented at an angle relative to said second plane;

a generally cylindrical inlet sleeve having an inner diameter and outer diameter, said inlet sleeve fixed to said inlet end of said panel assembly;

a generally rectangular aft end frame, said frame fixed to said exit end of said panel assembly;

a plurality of cooling holes in said panel assembly, each of said cooling holes having a diameter D and separated from the closest adjacent one of said cooling holes by a distance of at least P in the axial and transverse directions, said cooling holes extending from said outer wall to said inner wall, and oriented at an acute angle β

relative to said outer wall at the location of where said cooling hole penetrates said outer wall.

2. The transition duct of claim 1 wherein said acute angle β

is a maximum of 30 degrees.

3. The transition duct of claim 2 wherein said diameter D of said cooling holes is at least 0.040 inches.

4. The transition duct of claim 1 wherein said cooling holes are drilled in a direction from said outer wall towards said inner wall and angled in a direction towards said aft end frame.

5. The transition duct of claim 1 wherein said distance P in said axial and transverse directions is less than or equal to 15 times said cooling hole diameter D.

6. The transition duct of claim 1 wherein said panel assembly contains cooling holes covering at least 20% of said walls by surface area.

7. The transition duct of claim 1 wherein said panel assembly, inlet sleeve, and aft end frame are manufactured from a nickel-base superalloy such as Inconel 625.

8. The transition duct of claim 1 wherein said thickness is at least 0.125 inches.

9. An effusion cooled transition duct for transferring hot gases from a combustor to a turbine comprising:

a panel assembly comprising;

a first panel formed from a single sheet of metal;

a second panel formed from a single sheet of metal;

said first panel fixed to said second panel by a means such as welding thereby forming a duct having an inner wall, an outer wall, a thickness therebetween said walls, a generally cylindrical inlet end, and a generally rectangular exit end, said inlet end defining a first plane, said exit end defining a second plane, said first plane oriented at an angle relative to said second plane;

a first radius of curvature located along said first panel between said cylindrical inlet and said rectangular exit end;

a second radius of curvature located along said second panel between said cylindrical inlet end and said rectangular exit end;

a generally cylindrical inlet sleeve having an inner diameter and outer diameter, said inlet sleeve fixed to said inlet end of said panel assembly;

a generally rectangular aft end frame, said frame fixed to said exit end of said panel assembly;

a plurality of cooling holes in said panel assembly, each of said cooling holes having a diameter D and separated from the closest adjacent one of said cooling holes by a distance of at least P in the axial and transverse directions, said cooling holes extending from said outer wall to said inner wall, and oriented at an acute angle β

relative to said outer wall at the location of where said cooling hole penetrates said outer wall.

10. The transition duct of claim 9 wherein said acute angle β

is a maximum of 30 degrees.

11. The transition duct of claim 10 wherein said diameter D of said cooling holes is at least 0.040 inches.

12. The transition duct of claim 9 wherein said cooling holes are drilled in a direction from said outer wall towards said inner wall and angled in a direction towards said aft end frame.

13. The transition duct of claim 9 wherein said distance P in said axial and transverse directions is less than or equal to 15 times said cooling hole diameter D.

14. The transition duct of claim 9 wherein said panel assembly contains cooling holes covering at least 20% of said walls by surface area.

15. The transition duct of claim 9 wherein said panel assembly, inlet sleeve, and aft end frame are manufactured from a nickel-base superalloy such as Inconel 625.

16. The transition duct of claim 9 wherein said thickness is at least 0.125 inches.

17. The transition duct of claim 9 wherein said first radius of curvature is at least 10 inches and said second radius of curvature is at least 3 inches.