General Electric Company

Kwanwoo Kim

Fei Han

Shiva Kumar Srinivasan

Kapil Kumar Singh

Pradeep Naik

Steven Clayton Vise

Shai Birmaher

Thomas Edward Johnson

Clayton Stuart Cooper

Saket Singh

Karthikeyan Sampath

Jong Ho Uhm

Owen Graham

Michael Anthony Benjamin

Patrick Benedict Melton

Perumallu Vukanti

Sven Georg Bethke

Venkateswarlu Narra

Luis Flamand

Gilbert Otto Kraemer

Hiranya Kumar Nath

Abdul Rafey Khan

Donald Mark Bailey

Nicholas Ryan Overman

Nicholas Magina

Qingguo Zhang

David Kaylor Toronto

Sharath Nagaraja

Preetham Balasubramanyam

Vivekta Sharma

Ravindra Shankar Ganiger

Jonathan Dwight Berry

Benjamin Paul Lacy

Lewis Berkley Davis, Jr

Geoffrey David Myers

Alfred Albert Mancini

Nayan Vinodbhai Patel

Baifang Zuo

Allen Michael Danis

Duane Douglas Thomsen

Craig Alan Gonyou

Sarah Lori Crothers

Ertan Yilmaz

Sripathi Mohan

Robert Joseph Rohrssen

Balachandar Varatharajan

Raymond Floyd Martell

Mark Anthony Mueller

Ranganatha Narasimha Chiranthan

Quoc Hoai Nguyen

Andrew Joseph Wickersham

Gurunath Gandikota

Nishant Govindbhai Parsania

Anquan Wang

John Joseph Lynch

Mohan Krishna Bobba

Carolyn Ashley Antoniono

John Drake Vanselow

John Thomas Herbon

Donald Timothy Lemon

Dharmaraj Pachaiappan

Patrick Edward Pastecki

Varun Swaminathan Lakshmanan

Chad Holden Sutton

Narasimhan S Sahana

Changjin Yoon

Nan Zong

Praveen Babulal Jain

Dheeraj Sharma

Harris Daniel Abramson

Robert Andrew Stowers

Ajay Pratap Singh

James A Russo

Shanwu Wang

Venkat Narra

Ugandhar K Reddy

Whitney Epperson

Yongqiang Fu

Praveen Kumar Babulal Jain

Luis M Flamand

Shiva Srinivasan

Praveen Jain

Systems, apparatus, articles of manufacture, and methods are disclosed for an acoustic damping device. An example apparatus includes a first channel defining a first volume, the first channel open on a first end and closed on a second end, a second channel surrounding the first channel and defining a second volume, and a plurality of discs oriented within the first channel, respective discs of the plurality of discs including an opening in a center of the respective disc to allow at least one of a fluid or acoustic oscillation to move from the first end to the second end, the first channel including a plurality of apertures dispersed along an outer wall of the first channel and between the plurality of discs, the apertures to facilitate transfer of at least one of the fluid or the acoustic oscillation from the first channel to the second channel.

Acoustic damping device

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 flare cone for a mixer assembly includes an annular conical wall extending circumferentially about a mixer assembly centerline, the annular conical wall including a conical inner surface defining a conical opening of the annular conical wall, and an annular axial wall extending in a longitudinal direction with respect to the mixer assembly centerline, the annular axial wall disposed at a radially outward portion of the annular conical wall and connected to the annular conical wall. The annular conical wall and the annular axial wall define an annular step circumferentially about the mixer assembly centerline and extending upstream in the longitudinal direction between a downstream end of the annular conical wall and an aft surface of the annular axial wall.

Flare cone for a mixer assembly of a gas turbine combustor

A combustor for an aircraft gas turbine engine includes a dome structure, a swirler assembly connected to the dome structure, and a cowl connected to the dome structure and defining a plenum between the dome structure and the cowl, and surrounding the swirler assembly. The cowl includes an airflow opening through an upstream wall portion of the cowl for providing a flow of compressed air into the plenum. In addition, the cowl includes a cowl steam channel therewithin and a plurality of steam injection nozzles that provide a flow of steam from the cowl steam channel into the plenum.

Combustor for a gas turbine engine

A swirler assembly includes a swirler having a primary swirler with a primary swirler venturi, a swirler ferrule plate connected upstream to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an annular pressure drop cavity with oxidizer inlet orifices in fluid communication with the swirler, and at least one outlet orifice in fluid communication with the primary swirler venturi. A second flow of oxidizer to the swirler incurs a first pressure drop, a third flow of the oxidizer from the swirler to the annular pressure drop cavity incurs a second pressure drop, and a fourth flow of the oxidizer from the annular pressure drop cavity to the primary swirler venturi incurs a third pressure drop.

Coupling a fuel nozzle purge flow directly to a swirler

A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.

Multi pressure drop swirler ferrule plate

A gas turbine engine may include a combustion section having a fuel nozzle, a swirler, and a ferrule configured to mount and center the fuel nozzle with the swirler. The combustion section may further include a damper on a cold side of the combustion section. The damper may have an acoustic cavity, a damper neck, and a cavity feed hole. The damper may operate as Helmholtz cavity to absorb a hydrodynamic or acoustic instability present in a region within the swirler.

Damper for swirl-cup combustors

The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.

Gas turbine assemblies and methods

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.

Swirler with integrated damper

A fluid manifold assembly for a gas turbine engine, the fluid manifold assembly including a walled conduit assembly defining a fluid passage therewithin. The fluid passage defines a pair of ends separated by a length. A connecting conduit is coupled to the end of the fluid passage and to the length of the fluid passage.

Fluid manifold damper for gas turbine engine

A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.

Fuel delivery system for a gas turbine engine

The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.

Combustor acoustic damping structure

In one aspect the present subject matter is directed to a system for suppressing acoustic noise within a combustion section of a gas turbine. The system includes at least one static structure disposed forward of a combustion chamber defined within the combustion section. The static structure at least partially defines a diffuser cavity upstream of the combustion chamber. A baffle plate is coupled to the static structure. The baffle plate and the static structure at least partially define an air plenum within the combustion section forward of the combustion chamber. The baffle plate includes an aperture that provides for fluid communication between the diffuser cavity and the air plenum. The at least one static structure and the baffle plate define a Helmholtz resonator within the combustion section.

System for suppressing acoustic noise within a gas turbine combustor

An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure the tube end in fluidic communication with a fluid volume enclosed by a liner. The cavity opening is connected with the resonating cavity. The case includes a vented ferrule adpressed over a perforated region of the liner. The vented ferrule defines a ferrule opening that is aligned with the perforated region of the liner and the cavity opening to form the fluidic communication between the fluid volume and the resonating cavity.

High frequency acoustic damper for combustor liners

Growing community of inventors

Cincinnati, OH, United States of America

Kwanwoo Kim