General Electric Company

Vmware, Inc.

Saket Singh

Pradeep Naik

Rimple Rakeshkumar Rangrej

Perumallu Vukanti

Shai Birmaher

Karthikeyan Sampath

Steven Clayton Vise

Hiranya Kumar Nath

Ajoy Patra

Ravindra Shankar Ganiger

Michael Anthony Benjamin

Krishnendu Chakraborty

Ranganatha Narasimha Chiranthan

Clayton Stuart Cooper

Kwanwoo Kim

Manampathy Gangadharan Giridharan

Michael Terry Bucaro

R Narasimha Chiranthan

Daniel J Kirtley

Nicholas Ryan Overman

Veeraraju Vanapalli

Gurunath Gandikota

Rajendra Mahadeorao Wankhade

Deepak Ghiya

Narasimhan S Sahana

Neeraj Kumar Mishra

Vijayaraj Sukumar

Allen Michael Danis

Sripathi Mohan

Scott Matthew Bush

Hari Ravi Chandra

Arvind Kumar Rao

Ranjeet Kumar Mishra

Rimpie Rangrej

Gregory Allen Boardman

Joseph Zelina

David Albin Lind

Ammar Rizvi

Krishnendu Gorai

Dinesh Sharma

Girish Kamath Cannanore

Deepti Bhandari

Narasimha Chiranthan R

Veera Venkata Amarnath Manem

Balasubramaniam Venkatanarayanan

Aakash Bhattacharya

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 a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

Combustor for a gas turbine engine

An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

Gas turbine engine fuel nozzle having a secondary fuel passage through a swirler

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

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 combustor includes a combustion chamber and an annular dome. The combustion chamber includes an outer liner and an inner liner and has a combustion zone. The annular dome is coupled to the outer liner and the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases. A combustor steam system is in fluid communication with the combustion chamber. The combustor steam system includes a steam path defined by at least one of the outer liner, the inner liner, or the annular dome. The combustor steam system operably directs steam through the steam path from the at least one of the outer liner, the inner liner, or the annular dome and into the combustion chamber.

Combustor

A swirler assembly includes a primary swirler having a primary swirler connecting portion, a fuel nozzle connecting portion for connecting a fuel nozzle to the primary swirler, and a primary oxidizer flow passage that extends at least partially in the longitudinal direction, and a secondary swirler having a secondary swirler connecting member, where the primary swirler connecting portion and the secondary swirler connecting member engage to connect the primary swirler and the secondary swirler in the longitudinal direction, and to permit radial movement of the primary swirler with respect to the secondary swirler.

Floating primary vane swirler

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 liner assembly for a combustor. The liner assembly includes a liner defining a combustion chamber of the combustor. The liner includes a looped section at a forward end of the liner. The looped section includes one or more bends such that the looped section forms a compliant joint and vibrations are dampened through the liner downstream of the looped section.

Liner assembly for a combustor

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

Mixer vanes having a waveform profile

A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.

Combustion liner having a dilution passage

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

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Bengaluru, India

Saket Singh