Gas turbine assemblies and methods

Abstract

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.

What is claimed is: 
     
         1 . A gas turbine assembly comprising:
 a dome having an aperture configured to surround an injector assembly for a combustor, the dome having a front panel radially extending from the aperture and having a first cavity including a series of ducts, wherein 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.   
     
     
         2 . The gas turbine assembly of  claim 1 , wherein the first cavity extends along a circumference of a backside of the front panel. 
     
     
         3 . The gas turbine assembly of  claim 1 , wherein the first cavity extends along a portion of a circumference of a backside of the front panel. 
     
     
         4 . The gas turbine assembly of  claim 3 , wherein a volume of the first cavity and the diameter of the third duct are based on a target frequency indicative of a resonance. 
     
     
         5 . The gas turbine assembly of  claim 3 , wherein the dome includes a second cavity extending along a portion of a circumference of a backside of the front panel, the second cavity further having a second series of ducts, wherein a volume of the first cavity is based on a first target frequency and a volume of the second cavity is based on a second target frequency. 
     
     
         6 . The gas turbine assembly of  claim 1 , wherein the second set of ducts are configured to direct an airflow to reduce a thermal temperature of the dome. 
     
     
         7 . The gas turbine assembly of  claim 1 , wherein the first cavity is configured to adjust an amount of air pressure delivered to the combustor. 
     
     
         8 . A method comprising:
 providing a dome having aperture configured to surround an injector assembly for a combustor, the dome having a front panel extending radially from the aperture; and   coupling a first cavity to the front panel, wherein the first cavity includes a series of ducts, wherein a first duct is configured to receive airflow into the first cavity from the compressor, a second set of ducts are configured to direct an airflow to reduce a thermal temperature of the dome.   
     
     
         9 . The method of  claim 8 , wherein the first cavity includes a third duct configured to direct airflow to the combustor from the first cavity, wherein the third duct has a diameter larger than the second set of ducts. 
     
     
         10 . The method of  claim 9 , wherein the first cavity extends along a circumference of a backside of the front panel. 
     
     
         11 . The method of  claim 9 , wherein the first cavity extends along a portion of a circumference of a backside of the front panel. 
     
     
         12 . The method of  claim 9 , further comprising adjusting a volume of the first cavity and the diameter of the third duct based on a target frequency indicative of a resonance. 
     
     
         13 . The method of  claim 9 , wherein the second set of ducts are positioned about the third duct. 
     
     
         14 . The method of  claim 8 , further comprising coupling a second cavity to the first cavity, the second cavity having a third duct configured to receive airflow into the second cavity from the compressor, and a fourth duct configured to direct airflow to a combustor, wherein the fourth duct has a diameter larger than the second set of ducts. 
     
     
         15 . The method of  claim 13 , wherein the third duct interconnects the first and second cavities and is configured to direct airflow from the first cavity to the second cavity. 
     
     
         16 . The method of  claim 13 , wherein the front panel is angled to direct the airflow of the second set of ducts and the fourth duct away from the aperture. 
     
     
         17 . A dome assembly of a gas turbine assembly, the dome assembly comprising:
 a front panel radially extending from an aperture that surrounds an injector assembly of the gas turbine assembly, the front panel having first and second cavities with the first cavity having a first set of ducts configured to receive airflow into the first cavity from the compressor and a second set of ducts configured to direct airflow to a combustor, the second cavity having a third duct configured to receive airflow into the second cavity and a fourth duct configured to direct airflow to a combustor, wherein the fourth duct has a diameter larger than the second set of ducts.   
     
     
         18 . The dome assembly of  claim 18 , wherein the third duct interconnects the first and second cavities and is configured to direct airflow from the first cavity to the second cavity. 
     
     
         19 . The dome assembly of  claim 18 , wherein the second set of ducts are positioned about the fourth duct. 
     
     
         20 . The dome assembly of  claim 18 , wherein the front panel is angled to direct the airflow of the second set of ducts and the fourth duct away from the aperture.