Gas turbine assemblies and methods
The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
1. 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.
2. The method of claim 1 , wherein the first cavity extends along a circumference of a backside of the front panel.
3. The method of claim 1 , wherein the first cavity extends along a portion of a circumference of a backside of the front panel.
4. The method of claim 1 , further comprising adjusting a volume of the first cavity, a diameter of the first duct, and the diameter of each duct of the set of second ducts based on a target frequency indicative of a resonance.
5. The method of claim 1 , wherein the front panel is angled to direct the airflow of the set of second ducts and the fourth duct away from the aperture.