General Electric Company

Neeraj Kumar Mishra

Pradeep Naik

Saket Singh

Rimple Rakeshkumar Rangrej

Steven Clayton Vise

Perumallu Vukanti

Karthikeyan Sampath

Allen Michael Danis

Gurunath Gandikota

Scott Matthew Bush

Ranjeet Kumar Mishra

Arvind Kumar Rao

Hari Ravi Chandra

Nayan Vinodbhai Patel

Duane Douglas Thomsen

Daniel J Kirtley

Adam Robert Kahn

Balasubramaniam Venkatanarayanan

A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.

Combustor swirler with vanes incorporating open area

A gas turbine combustor includes a main mixer for providing an air flow to mix with a fuel flow in a combustor. The main mixer includes an annular mixer body, a plurality of mixer vanes located circumferentially around the annular mixer body, and a plurality of wedges extending radially outward from each of the plurality of mixer vanes. At least one of the wedges includes serrations. The air flow through the main mixer enters the main mixer at a leading edge of the mixer vane, flows over the plurality of wedges, and exits the mixer vanes at a trailing edge of the main mixer. The wedges create vortices in the air flow to provide a uniform fuel-air flow.

Mixer vanes

A dome assembly for a combustor includes: at least one swirler assembly including: at least one swirler including a plurality of swirl vanes arrayed about an axis, the plurality of swirl vanes oriented so as to impart a tangential velocity to air passing through the swirler parallel to the axis; each of the plurality of swirl vanes having a thickness and including a plurality of edges which collectively define a peripheral boundary of the respective swirl vane; wherein at least a selected one of the plurality of swirl vanes includes at least one void passing through the thickness of the selected swirl vane, the void disposed within the peripheral boundary of the selected swirl vane.

The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.

Purge cooling structure for combustor assembly

Growing community of inventors

Bengaluru, India

Neeraj Kumar Mishra