Damper for swirl-cup combustors
AssigneeGeneral Electric Company
InventorsKwanwoo Kim, Clayton Cooper, Steven Vise, Shai Birmaher, Pradeep Naik, Andrew Wickersham
Life of this patent
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Abstract
A gas turbine engine may include a combustion section having a fuel nozzle, a swirler, and a ferrule configured to mount and center the fuel nozzle with the swirler. The combustion section may further include a damper on a cold side of the combustion section. The damper may have an acoustic cavity, a damper neck, and a cavity feed hole. The damper may operate as Helmholtz cavity to absorb a hydrodynamic or acoustic instability present in a region within the swirler.
Claims20
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.
A damper for suppressing a hydrodynamic or acoustic instability in a combustion chamber of a gas turbine engine, the damper comprising:
- a ferrule configured to mount and center a fuel nozzle in a swirler, the ferrule including:
- an acoustic cavity having a volume;
- a cavity feed hole configured to provide a first portion of air to the acoustic cavity;
- and
- a damper neck,
- wherein the acoustic cavity, the cavity feed hole, and the damper neck are integral and unitary within a body of the ferrule,
- wherein the acoustic cavity, the cavity feed hole, and the damper neck are dimensioned to absorb a frequency of hydrodynamic or acoustic instability in the combustion chamber, and
- wherein a downstream wall of the ferrule is axially forward of an upstream wall of the swirler, and the swirler directs a second portion of the air to a region within an interior of the swirler 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.
A gas turbine engine comprising:
- a fuel nozzle mounted in a ferrule;
- a swirler configured to mix a first portion of air and fuel in a combustion section;
- and
- a damper integral and unitary with the ferrule,
- wherein the damper provides a second portion of the air and is dimensioned to absorb a frequency of hydrodynamic or acoustic instability in the swirler, and
- wherein a downstream wall of the ferrule is axially forward of an upstream wall of the swirler, and the swirler directs the first portion of the air to a region within an interior of the swirler 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 a combustion chamber of the combustion section.
Dependencies are inferred from the claim text.