General Electric Company

Ranganatha Narasimha Chiranthan

Pradeep Naik

Saket Singh

Rimple Rakeshkumar Rangrej

Hiranya Kumar Nath

Perumallu Vukanti

Karthikeyan Sampath

Ravindra Shankar Ganiger

Shai Birmaher

Steven Clayton Vise

Ajoy Patra

Michael Anthony Benjamin

Gregory Allen Boardman

Clayton Stuart Cooper

Kwanwoo Kim

Sibtosh Pal

Allen Michael Danis

Veeraraju Vanapalli

David Albin Lind

Krishnendu Chakraborty

Girish Kamath Cannanore

Vijayaraj Sukumar

Rimpie Rangrej

Deepti Bhandari

Ugandhar K Reddy

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 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 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 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 combustor for a turbine engine includes a main combustion chamber, an annular dome, and a secondary combustion chamber positioned downstream of the annular dome. A plurality of first mixing assemblies are disposed through the annular dome and include a pilot mixer. The pilot mixer injects a pilot mixer fuel-air mixture axially into the main combustion chamber and generates a first recirculation zone within the main combustion chamber. A plurality of second mixing assemblies are disposed at the secondary combustion chamber axially aft of the first mixing assemblies and include a main mixer. The main mixer injects a main mixer fuel-air mixture into the secondary combustion chamber to produce combustion gases and to generate a second recirculation zone within the secondary combustion chamber axially aft of the first recirculation zone. The secondary combustion chamber injects the combustion gases into the main combustion chamber.

Turbine engine including a combustor

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 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.

Wavy annular dilution slots for lower emissions

A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.

Combustor liner having cooling dispersing member for localized liner cooling

A liner for a combustor in a gas turbine engine. The liner may include a liner body having a cold side and a hot side. The liner may include a dilution opening and a passage extending through the liner body. The passage may be positioned adjacent the dilution opening. The passage may be angled with respect to an interior surface of the liner body. A dilution flow may flow through the dilution opening from the cold side to the hot side and a secondary flow may flow through the passage from the cold side to the hot side. The secondary flow may exit into the hot side behind the dilution flow and may suppresses wakes formed behind the dilution flow on the hot side of the liner.

A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.

Swirler opposed dilution with shaped and cooled fence

A ferrule in a fuel-air mixer assembly. The ferrule includes a body having (i) a plurality of channels having sidewalls, the plurality of channels leading to a corresponding plurality of exit openings, the plurality of channels configured to guide a first airflow therein and (ii) a plurality of cascade holes formed within the sidewalls of the plurality of channels and defining a plurality of passageways therein that are transverse to the plurality of channels. The ferrule also includes a plurality of airflow modifiers provided within the plurality of channels. The plurality airflow modifiers are configured to reduce a velocity of the first airflow when the first airflow exits through the plurality of exit openings and to generate low velocity vortex pairs to reduce interaction of the first airflow with a second airflow provided through primary vanes located downstream of the plurality of exit openings of the plurality of channels.

Ferrule for fuel-air mixer assembly

A swirler with integrated damper may include a primary swirler vane having a primary air passage, a secondary swirler vane having a secondary air passage, and a damper within the primary swirler vane, the secondary swirler vane, or both the primary swirler vane and the secondary swirler vane. The damper may include a series of cavities. The damper is configured to absorb one or more frequencies present in an air flow through the primary air passage, the secondary air passage, or both the primary air passage and the secondary air passage.

Growing community of inventors

Karnataka, India

Ranganatha Narasimha Chiranthan