Slot cooled combustor liner

• US 6,543,233 B2
• Filed: 02/09/2001
• Issued: 04/08/2003
• Est. Priority Date: 02/09/2001
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Kutter, Ella Christine, Young, Craig Douglas
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US09/783,278
• Publication Number:
  US 20020108374A1
• Time in Patent Office: 788 Days
• Field of Search: 607/52, 607/54, 607/55, 607/56, 607/57
• US Class Current: 60/752
• CPC Class Codes: F23R 3/08 between annular flame tube sections, e.g. flame tubes with telescopic sections
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A combustor liner for use in a gas turbine engine includes a first annular panel section having a forward end, an aft end and a first cooling nugget located at the forward end thereof, and a second annular panel section having a forward end, an aft end and a second cooling nugget located at the forward end thereof. The second panel section is joined at its forward end to the aft end of the first panel section. A first row of cooling holes is located in the first cooling nugget, and a second row of cooling holes is located in the second cooling nugget. A group of dilution holes is located in the first panel section. The dilution holes are located at the aft end of the first panel section, immediately upstream of the second cooling nugget. Furthermore, each one of the dilution holes defines an aftmost edge, and all of the aftmost edges are axially aligned, even if the dilution holes have different hole diameters.

Claims

1. A gas turbine combustor liner comprising:

a first annular panel section having a forward end and an aft end;

a second annular panel section having a forward end and an aft end, said second panel section being joined at its forward end to said aft end of said first panel section;

a group of dilution holes located in said first panel section, at least one of said dilution holes having a larger diameter than other ones of said dilution holes, wherein each one of said dilution holes defines an aftmost edge and all of said aftmost edges are axially aligned;

a third annular panel section having a forward end and an aft end, said third panel section being joined at its forward end to said aft end of said second panel section; and

a second group of dilution holes located in said second panel section, at least one of said second dilution holes having a larger diameter than other ones of said second dilution holes, wherein each one of said second dilution holes defines an aftmost edge and all of said aftmost edges of said second dilution holes are axially aligned.

2. The liner of claim 1 wherein said dilution holes are located at said aft end of said first panel section.

3. The liner of claim 1 further comprising a cooling nugget located at said forward end of said second panel section and a row of cooling holes located in said cooling nugget, said dilution holes being located immediately upstream of said cooling nugget.

4. The liner of claim 3 wherein each one of said dilution holes has a larger diameter than any one of said cooling holes.

5. The liner of claim 1 wherein said second dilution holes are located at said aft end of said second panel section.

6. A gas turbine combustor liner comprising:

a first annular panel section having a forward end and an aft end and a first cooling nugget located at said forward end thereof;

a first row of cooling holes located in said first cooling nugget;

a second annular panel section having a forward end and an aft end and a second cooling nugget located at said forward end thereof, said second panel section being joined at its forward end to said aft end of said first panel section;

a second row of cooling holes located in said second cooling nugget;

a group of dilution holes located in said first panel section, said dilution holes being located at said aft end of said first panel section, immediately upstream of said second cooling nugget, wherein at least one of said dilution holes has a larger diameter than other ones of said dilution holes, and each one of said dilution holes defines an aftmost edge, and all of said aftmost edges are axially aligned;

a third annular panel section having a forward end and an aft end and a third cooling nugget located at said forward end thereof, said third panel section being joined at its forward end to said aft end of said second panel section; and

a second group of dilution holes located in said second panel section, said second dilution holes being located at said aft end of said second panel section, immediately upstream of said third cooling nugget, wherein at least one of said second dilution holes has a larger diameter than other ones of said second dilution holes, and each one of said second dilution holes defines an aftmost edge, and all of said aftmost edges are axially aligned.

7. The liner of claim 6 wherein each one of said dilution holes has a larger diameter than any one of said cooling holes.