Turbine combustion system liner

A turbine combustion chamber liner comprising:

• a tubular wall having a forward section and an aft section;
• a first array of axial cooling fins formed on an outer surface of the aft section;
• a plurality of respective grooves formed between cooling fins within the first array of axial cooling fins;
• a tubular support ring covering the first array of axial cooling fins;
• a plurality of coolant inlet holes formed within a forward end of the tubular support ring for admitting a coolant onto the first array of axial cooling fins and the plurality of respective grooves;
• and
• wherein the first array of axial cooling fins and the plurality of respective grooves are formed straight along a longitudinal axis of the tubular wall having smooth surfaces devoid of turbulators.

A turbine combustion chamber section comprising:

• an outer surface defining a circumference of the section;
• a plurality of axial cooling fins formed on the outer surface, the plurality of axial cooling fins extending substantially parallel to a longitudinal axis of the section and having smooth surfaces devoid of turbulators;
• and
• a plurality of longitudinal grooves formed between ones of the plurality of axial cooling fins, the plurality of longitudinal grooves having smooth surfaces devoid of turbulators whereby a coolant flowing over the outer surface convectively cools the section;
• a plurality of bumpers formed on ones of the plurality of axial cooling fins;
• and
• circumferential grooves formed between ones of the plurality of bumpers whereby the coolant may flow both axially along the plurality of longitudinal grooves and circumferentially among the plurality of longitudinal grooves by passing through the circumferential grooves.