US 11,686,474 B2
Damper for swirl-cup combustors
Kwanwoo Kim, Cincinnati, OH (US); Clayton Cooper, Loveland, OH (US); Steven Vise, Loveland, OH (US); Shai Birmaher, Cincinnati, OH (US); Pradeep Naik, Karnataka (IN); and Andrew Wickersham, Liberty Township, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 4, 2021, as Appl. No. 17/192,613.
Prior Publication US 2022/0282870 A1, Sep. 8, 2022
Int. Cl. F23R 3/28 (2006.01); F02C 7/22 (2006.01); F23M 20/00 (2014.01)
CPC F23R 3/286 (2013.01) [F02C 7/22 (2013.01); F23M 20/005 (2015.01); F05D 2240/35 (2013.01); F05D 2260/963 (2013.01); F23R 2900/00014 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a combustion section having a cold side and a hot side, wherein the hot side defines a combustion chamber and the cold side of the combustion section comprises:
a fuel nozzle;
a swirler extending from a forward end to an aft end;
a ferrule located upstream of the forward end of the swirler and configured to mount and center the fuel nozzle with the swirler; and
a damper located directly upstream of the forward end of the swirler and having an acoustic cavity, a damper neck, and a damper neck opening,
wherein the damper provides a first portion of air, operates as a Helmholtz cavity, and is configured to absorb a hydrodynamic or acoustic instability present in a region within an interior of the swirler, and
wherein the swirler directs a second portion of the air to the region in which fuel from the fuel nozzle is mixed with the first portion of the air and the second portion of the air before entering the combustion chamber.