General Electric Company

Arvind Namadevan

Ravindra Shankar Ganiger

Arnab Sen

Hiranya Kumar Nath

Rajesh Kumar

Jeffrey Douglas Rambo

Scott Alan Schimmels

Mohan Kannaiah Raju

Subramani Adhiachari

Dharmaraj Pachaiappan

Thomas DeWitt Woodrow

Prasant Bilaiya

Bhaskar Nanda Mondal

Weize Kang

Rajendra Mahadeorao Wankhade

Nageswar Rao Ganji

Shankar Jayaraman

Hari Shanker Thakur

Jeffrey D Carnes

Steven Mark Ballman

Keith Blodgett

Charles Eric Lavender

Sivaprakaash Karuppanchetty

Siddhartha Pal

Hari Shankar Thakur

Urmi Tejaswini

Mayur Ghawat

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 lock lug for inhibiting movement of a plurality of rotor blades includes a body and an engagement mechanism. The body is sized and configured to be received within the rim slot of the rotor disk and defines a dovetail receiving aperture. The engagement mechanism extends from the body and has a retracted configuration configured to allow entry and exit of a dovetail of at least one or more of the plurality of rotor blades into and out of the dovetail receiving aperture and an extended configuration configured to block the dovetail from entering the dovetail receiving aperture.

Methods and apparatuses for blade locking

A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube and a movable sleeve. The tube has an interior surface defining a flow passage for the hydrocarbon fluid. The movable sleeve is positioned within the flow passage to abut the interior surface and is movable along the interior surface in response to a change in an operating characteristic of the conduit to break-up deposits on the interior surface.

A check valve assembly for a supply pipe. The check valve assembly includes a hinge pin, a first flapper, and a second flapper. The first flapper is pivotally coupled to the second flapper with the hinge pin. The check valve assembly also includes a stopper located between the first flapper and the second flapper. The stopper is configured to limit movement of the first flapper and the second flapper. The check valve assembly further includes a plate assembly located downstream of the stopper. The plate assembly is configured to break vortices formed in a fluid flow across the first flapper and the second flapper.

Check valve assembly

An aspect of the present disclosure is directed to a system for reducing thermal gradient at a heat engine. The heat engine includes a rotor assembly with a rotor disk and a seal assembly is provided. An interfacing structure at least partially surrounds the rotor assembly at the seal assembly. The seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition. A fluid supply manifold is connected to the rotor assembly and is extended at least partially along a radial direction from the first cavity to an outlet opening in thermal communication with the rotor disk of the rotor assembly.

System for rotor assembly thermal gradient reduction

An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area. A gas turbine engine includes a source of high pressure air, a region of low pressure air, and an ejector assembly, the ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, the primary fluid inlet in fluid communication with the source of high pressure air, a secondary nozzle in fluid communication with a secondary fluid inlet, the secondary fluid inlet in fluid communication with the region of low pressure air, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.

Variable area ejector

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.

Aircraft having an engine wing assembly

The present disclosure is directed to a system for mitigating rotor bow at a turbine engine. The system includes a casing circumferentially surrounding a rotor assembly in which a heat pipe is attached to the casing and extended circumferentially around the rotor assembly.

Heat pipe in turbine engine

A compressor for a turbine engine comprises radially spaced inner and outer bands defining a flow path between them, at least one vane extending between the inner and outer bands, a seal adjacent the inner band, and a cooling air circuit through the inner band proximate the seal.

Turbine engine compressor with a cooling circuit

Growing community of inventors

Bengaluru, India

Arvind Namadevan