Patent ID: 8336312
Filing Date: 2012-12-25
Classification: F02C,F05D,F23M,F23R

Abstract:
1. A can-annular gas turbine engine comprising: a casing defining an annulus for receiving air flow from a compressor; a combustor basket supported within the casing; a swirler assembly located within the basket and having an air inlet and an outlet located in a combustion chamber, the swirler assembly configured to discharge a fuel/air mixture from the outlet downstream into the combustion chamber; an acoustic filter comprising a Herschel-Quincke tube having a major length and opposing first and second open ends at opposing ends of the major length, and a centerline of the tube extending centrally within the tube along the major length, wherein the centerline of the tube passes through each of the first and second open ends of the tube, and wherein the first open end is located at the annulus and the second open end is located within an area surrounded by the combustor basket and is in fluid communication with and upstream of the combustion chamber; and wherein the swirler assembly is mounted to a base plate extending within the combustor basket, and the major length of the tube extends through an air inlet chamber upstream from the base plate, the second end of the tube passes through the base plate and the second end of the tube is located at a downstream side of the base plate and upstream from a flame front region in the combustion chamber.