General Electric Company

Rimple Rakeshkumar Rangrej

Pradeep Naik

Saket Singh

Perumallu Vukanti

Ravindra Shankar Ganiger

Hiranya Kumar Nath

Karthikeyan Sampath

Shai Birmaher

Ranganatha Narasimha Chiranthan

Ajoy Patra

Krishnendu Chakraborty

Michael Anthony Benjamin

Steven Clayton Vise

Daniel J Kirtley

Veeraraju Vanapalli

Deepak Ghiya

Neeraj Kumar Mishra

Allen Michael Danis

Gurunath Gandikota

Rajendra Mahadeorao Wankhade

Scott Matthew Bush

Ranjeet Kumar Mishra

Arvind Kumar Rao

Hari Ravi Chandra

Narasimhan S Sahana

Vijayaraj Sukumar

Gregory Allen Boardman

Joseph Zelina

Sripathi Mohan

Veera Venkata Amarnath Manem

Balasubramaniam Venkatanarayanan

Narasimha Chiranthan R

A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. The outer liner has an annular outer liner slot dilution opening, with a plurality of outer liner swirl vanes disposed within the annular outer liner slot dilution opening. The inner liner of the combustor liner includes an annular inner liner slot dilution opening, and also includes a plurality of inner liner swirl vanes disposed within the annular inner liner slot dilution opening.

Annular combustor dilution with swirl vanes for lower emissions

In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.

Components for combustor

A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.

Combustor deflector assembly

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 combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.

Combustor with secondary fuel nozzle in dilution fence

A main mixer for an engine. The main mixer includes a plurality of mixer vanes located circumferentially around a mixer body. Each mixer vane includes a waveform profile. The waveform profile detaches or trips a boundary layer of an air flow across the mixer vane such that the waveform profile introduces turbulence into the air flow.

Mixer vanes having a waveform profile

A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.

Varying dilution hole design for combustor liners

A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side, a dilution opening extending through the liner body, a first passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, and a second passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, the second passage being separate from the first passage and being located on a diametrically opposing side of the dilution opening from the first passage. A dilution flow flows through the dilution opening from the cold side to the hot side and a secondary flow flows through the first passage and the second passage from the cold side to the hot side.

Combustion liner

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 combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

Combustor for a gas turbine engine

A combustor for a gas turbine has a combustor liner including an upstream liner portion, and a downstream liner portion. The upstream liner portion includes an outer shell and a heat shield panel, with a baffle cavity therebetween. The outer shell includes an outer shell cooling opening for providing a flow of compressed air to the baffle cavity, and the heat shield panel includes a heat shield panel cooling opening at a downstream end of the heat shield panel. A fence is arranged at a downstream side of the heat shield panel cooling opening and extends beyond a hot side surface of the heat shield panel into a combustion chamber. The heat shield panel cooling opening provides a flow of the compressed air therethrough from the baffle cavity for cooling of the heat shield panel and for providing at least partial dilution of combustion gases within the combustion chamber.

Combustor having dilution cooled liner

A combustor for a gas turbine engine has a combustor liner that has a cold surface side and a hot surface side, the liner defining an upstream end and a downstream end, and a dilution opening through the combustor liner. The dilution opening includes a main dilution hole portion having an upstream edge and a downstream edge, a notched portion disposed at the upstream edge and extending upstream from the upstream edge, the notched portion being in fluid communication with the main dilution hole portion, and a slotted portion disposed at the downstream edge and extending downstream of the downstream edge, the slotted portion being in fluid communication with the main dilution hole portion.

Dilution air inlets with notched tip and slotted tail for combustor

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.

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Bengaluru, India

Rimple Rakeshkumar Rangrej