General Electric Company

Thomas Malkus

Trevor Howard Wood

Giridhar Jothiprasad

Kishore Ramakrishnan

Ravindra Shankar Ganiger

Hiranya Kumar Nath

Ambika Shivamurthy

Ramakrishna Venkata Mallina

Nageswar Rao Ganji

Nicholas Joseph Kray

Darren Lee Hallman

Changjie Sun

Jixian Yao

Justin John Gambone, Jr

Lana Maria Osusky

Li Zheng

Gregory Alexander Natsui

Keith Edward James Blodgett

Mitchell Jay Headley

Jeffrey D Carnes

Christopher E LaMaster

A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.

Circumferentially varying fan casing treatments for reducing fan noise effects

Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly a variable bleed valve (VBV) door corresponding to a bleed port and a first unison ring, the VBV door coupled to the first unison ring, the first unison ring to move in a circumferential direction between a first position and a second position causing the VBV door to move between the first position and the second position.

Bleed valve assemblies

Compact bleed valve assemblies are disclosed. An example turbine engine comprises a rotor blade having an axial chord (C) measured at a tip of the rotor blade, and a variable bleed valve (VBV) including a VBV port defining a bleed flowpath and an exit angle (β) for bleed air exiting the VBV port, the VBV port including a forward entrance edge and an aft exit edge and a first length (LA) therebetween, and a VBV door corresponding to the VBV port, the VBV door to generate a bleed cavity having a bleed cavity area (BA) in the VBV port when the VBV is in a closed position, the VBV door to move between an open position and the closed position at a rotation angle (Δθ), the VBV door to extend a distance (LA) beyond the first length (LA), wherein and wherein

Compact bleed valve assemblies

A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.

Reverse thrust turbofan engine

A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.

Cowl assembly for a propulsor

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

A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.

Thermal management system for a gas turbine engine

A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.

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Albany, NY, United States of America

Thomas Malkus