General Electric Company

Karthikeyan Sampath

Perumallu Vukanti

Pradeep Naik

Steven Clayton Vise

Saket Singh

Michael Anthony Benjamin

Hiranya Kumar Nath

Ravindra Shankar Ganiger

Rimple Rakeshkumar Rangrej

Shai Birmaher

Clayton Stuart Cooper

Ajoy Patra

Veeraraju Vanapalli

Allen Michael Danis

Ranganatha Narasimha Chiranthan

Gurunath Gandikota

Deepak Ghiya

Kwanwoo Kim

Daniel J Kirtley

Rajendra Mahadeorao Wankhade

Nicholas Ryan Overman

Sripathi Mohan

Bhaskar Nanda Mondal

Sibtosh Pal

Atanu Saha

Andrew Joseph Wickersham

Krishnendu Chakraborty

Scott Matthew Bush

Varun Swaminathan Lakshmanan

Mayank Krisna Amble

Hari Ravi Chandra

Sanjeev Sai Kumar Manepalli

Arvind Kumar Rao

Ranjeet Kumar Mishra

Narasimhan S Sahana

Neeraj Kumar Mishra

Vijayaraj Sukumar

Michael Terry Bucaro

Joseph Zelina

Craig Douglas Young

Arthur Wesley Johnson

R Narasimha Chiranthan

Jayanth Sekar

Habeeb Kunnummal Manat

Ravi Chandra

Veera Venkata Amarnath Manem

Michael Pedota

Balasubramaniam Venkatanarayanan

Girish Venkata Satya Sesha Goda

Ugandhar K Reddy

A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section including a primary combustor liner having an inner liner and an outer liner. A dome wall and a dome inlet are located in the dome wall. At least one opening is located in the outer liner downstream from the dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.

Combustion section with a primary combustor and a set of secondary combustors

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

An annular dome assembly for a combustor. The annular dome assembly includes an annular dome including one or more dome panels defining the annular dome. A first dome panel includes a dome upstream surface and a dome downstream surface opposite the dome upstream surface. One or more dome arms extend from the dome upstream surface. One or more apertures extend from the dome upstream surface to the dome downstream surface. The annular dome assembly also includes a deflector assembly including one or more deflector panels defining the deflector assembly. A first deflector panel includes a deflector upstream surface and a deflector downstream surface opposite the deflector upstream surface. One or more deflector arms extend from the deflector upstream surface. Each of the one or more deflector arms are mounted within a respective aperture of the annular dome.

Annular dome assembly for a combustor

A gas turbine engine comprising a compressor section, a combustion section, and a turbine section in a serial flow arrangement, with the combustion section comprising a combustor liner that at least partially defines a combustion chamber; and a gaseous fuel nozzle assembly, comprising: a steam supply to supply steam; a hydrogen fuel supply to supply gaseous hydrogen fuel; and a fuel nozzle body fluidly coupled with the steam supply and the hydrogen fuel supply.

Gas turbine and fuel nozzle assembly for mixing hydrogen fuel and steam to control flame speed

A turbine engine has a compression section, a combustion section, and a turbine section in serial flow arrangement. The combustion section has a combustion liner and dome wall collectively forming at least a portion of a combustion chamber. The combustion section has a fuel nozzle assembly. The fuel nozzle assembly has a compressed air tube, and a body. The body defining a gaseous fuel channel exhausting into the combustion chamber.

Turbine engine having a combustion section with a fuel nozzle assembly

A combustor for a gas turbine includes a combustor liner, an outer casing surrounding the combustor liner, an ignitor housing extending through an ignitor opening through the liner, and an ignitor disposed within the ignitor housing. The ignitor housing includes a housing wall including at least one airflow inlet passage on a downstream side of the housing wall and arranged within the outer flow passage, and at least one cooling passage on the downstream side within the housing wall. The at least one cooling passage extends along a length of the ignitor housing from the at least one airflow inlet passage and through the inner end of the ignitor housing, the at least one cooling passage being in fluid communication with the at least one airflow inlet passage.

Ignitor housing for a combustor of a gas turbine

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 turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini 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 liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

Combustor for a gas turbine engine

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 liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

Swirler-ferrule assembly

A combustor liner for a gas turbine includes a liner at least partially defining a combustion chamber. The liner includes a plurality of dilution openings therethrough, at least one dilution opening of the plurality of dilution openings defined by (a) a main dilution opening portion defining a main dilution opening perimeter, and (b) a plurality of secondary dilution opening portions arranged about the main dilution opening perimeter and extending outward from the main dilution opening portion.

Combustor liner having shaped dilution openings

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.

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

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Bengaluru, India

Karthikeyan Sampath