Gas turbine assemblies and methods

A method comprising:

• providing a dome having (a) an aperture configured to surround a combustor injector assembly, (b) a front panel extending radially from the aperture, and (c) a lip member extending from the aperture, a gap being defined between the front panel and the lip member and a radially outer end of the gap being open to a combustor combustion-chamber;
• coupling a first cavity to the front panel, wherein the first cavity includes a series of ducts, wherein a first duct of the series of ducts receives airflow into the first cavity from a compressor, and a set of second ducts directing the airflow from the first cavity into the gap to reduce a thermal temperature of the dome;
• coupling a second cavity to the first cavity, the second cavity having a third duct receiving airflow into the second cavity from the compressor, and a fourth duct radially outward from the set of second ducts and directing the airflow from the second cavity to said combustor combustion-chamber, providing the fourth duct with a diameter larger than a diameter of each duct of the set of second ducts;
• and
• angling the lip member to direct the airflow from the first cavity away from the aperture,
• wherein the front panel provides a downstream wall of the first cavity and the second cavity, the first cavity is between a portion of the second cavity and the front panel.