Patent ID: 6543233
Filing Date: 2003-04-08
Classification: F23R,Y02T

Abstract:
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.