General Electric Company

Hiranya Kumar Nath

Ravindra Shankar Ganiger

Pradeep Naik

Michael Anthony Benjamin

Perumallu Vukanti

Karthikeyan Sampath

Rimple Rakeshkumar Rangrej

Saket Singh

Daniel J Kirtley

Shai Birmaher

Rajendra Mahadeorao Wankhade

Ajoy Patra

Steven Clayton Vise

Nageswar Rao Ganji

Sripathi Mohan

Clayton Stuart Cooper

Trevor Howard Wood

Ranganatha Narasimha Chiranthan

Gurunath Gandikota

Veeraraju Vanapalli

Ambika Shivamurthy

Deepak Ghiya

Scott Alan Schimmels

Sibtosh Pal

Rajesh Kumar

Arvind Namadevan

Vijayaraj Sukumar

Girish Kamath Cannanore

Kwanwoo Kim

Joseph Zelina

R Narasimha Chiranthan

Nicholas Ryan Overman

Giridhar Jothiprasad

Paul Mathew

Mohan Kannaiah Raju

Thomas Malkus

Subramani Adhiachari

Krishnendu Chakraborty

Dharmaraj Pachaiappan

Thomas DeWitt Woodrow

Narasimhan S Sahana

Deepti Bhandari

Narasimha Chiranthan R

Prasant Bilaiya

Nicholas Joseph Kray

David Raju Yamarthi

Manampathy Gangadharan Giridharan

Michael Terry Bucaro

Kudum Shinde

Atanu Saha

Craig Alan Gonyou

Hejie Li

Viswanadha Gupta Sakala

Prateek Jalan

Michael Joseph Murray

Anquan Wang

Kirti Arvind Petkar

Mayank Krisna Amble

Arvind Kumar Rao

Hari Ravi Chandra

Jonathan K Remer

Rachamadugu Sivaprasad

Srinivas Nuthi

Rameshkumar Muthuvel Chandrasekaran

Narayanan Janakiraman

Vivekta Sharma

Veera Venkata Amarnath Manem

Habeeb Kunnummal Manat

Asim Ghosal

Daniel D Brown

Sreerama Prasad Ramaswamy

Urmi Tejaswini

A multi-fuel combustion system for a turbine engine, the multi-fuel combustion system having a combustion chamber formed by a combustor liner. The combustion chamber defines a first combustion zone and a second combustion zone. A first fuel system is fluidly coupled with the first combustion zone, where a rotary fuel slinger provides a first fuel to the first combustion zone. A second fuel system is fluidly coupled with the second combustion zone, where a gaseous fuel injector provides a second fuel to the second combustion zone.

Multi-fuel combustion system

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

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 turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel mixer. The fuel mixer can include an outer wall defining a longitudinal direction and having a mixture outlet, a first compressed air flow passage, and a second compressed air flow passage.

Turbine engine fuel mixer

A combustor for a gas turbine includes a dome structure including a dome-side swirler opening therethrough, and a deflector connected to the dome structure. The deflector includes a deflector-side swirler opening therethrough and a deflector-dome connecting member arranged at the deflector-side swirler opening. The deflector-dome connecting member is connected with the dome-side swirler opening via a snap-fit type connection.

Dome-deflector for a combustor of a gas turbine

A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.

Coupling assembly for a turbine engine

A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube and a mesh. The tube has an interior surface defining a flow passage for the hydrocarbon fluid. The mesh is positioned within the flow passage to abut the interior surface and movable along the interior surface to break-up deposits on the interior surface. The mesh is characterized by a mesh activation parameter (MAP) from one ten thousandths to six tenths.

Self-cleaning conduits for hydrocarbon fluids

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 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 combustor of a turbine engine has a combustion chamber for combusting fuel and air, generating heat. A fuel nozzle-mixer assembly mixes and injects fuel and air into the combustion chamber for combustion. The assembly has a heat shield at an aft end for shielding the assembly from the heat. A centerbody outer shell defines a cooling air flow cavity. A cooling air flow gap is defined between the centerbody outer shell and the heat shield. The centerbody outer shell has cooling air exit holes between the cooling air flow cavity and the cooling air flow gap, the air passing through the cooling air exit holes and into the cooling air flow gap. The cooling air exits the cooling air flow gap at a cooling air exit angle, the cooling air exit angle having a non-zero axially aft component, displacing the combustion downstream, to protect the assembly.

Turbine engine combustor including a heat shield

A dome-deflector assembly for a combustor of a gas turbine includes a dome portion having a dome-side swirler opening therethrough, and a deflector portion having a deflector-side swirler opening therethrough. The dome portion and the deflector portion are connected together to form a dome-deflector cavity therebetween. The deflector portion includes a first-side surface and a second-side surface, the second-side surface being arranged within the dome-deflector cavity, and the second-side surface including a plurality of stress-relief contours arranged in a pattern about the deflector-side swirler opening.

Dome-deflector assembly for a combustor of a gas turbine

This disclosure is directed to cooling systems for turbomachine seal assemblies. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. During operation of the turbomachine, the components of the seal assemblies generate heat, which is removed from the seal assembly by the cooling systems of this disclosure. In some examples, the cooling system includes a reservoir of lubricant that is distributed to a face of one of the components of the seal assembly. In other examples, the cooling system includes a lattice structure capable of retaining lubricant against the components of the seal assembly, or a pressurized jet of lubricant directed against the components of the seal assembly. The cooling systems can further include a combination of deflectors, hairpin members, and channels for distributing the lubricant to the components of the seal assemblies.

Cooling system for seal assemblies

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 combustion section of a turbine engine having a primary combustion chamber and a secondary combustion chamber. The primary combustion chamber is defined, at least in part, by a combustor liner and a dome wall. A primary fuel nozzle having an outlet is located at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber. At least one opening located in an outer liner axially aft of the dome wall fluidly couples the secondary combustion chamber and the primary combustion chamber. A set of secondary fuel nozzles are fluidly coupled with the secondary combustion chamber.

Combustion section with a primary combustion chamber and a secondary combustion chamber

Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

Aero-acoustically dampened bleed valve

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Bengaluru, India

Hiranya Kumar Nath