General Electric Company

General Electric Company Polska Sp. Z O.o.

Ge Avio S.r.l.

Tomasz Iglewski

Arthur William Sibbach

Vincenzo Martina

Michal Filipkowski

Aleksander Piotr Pasieczny

A screen for an air intake portion of a machine is provided. The screen includes an assembly of screen members that form a plurality of screen cells, wherein at least a portion of the screen cells define an irregular configuration.

Skeleton screen for an air intake portion of a machine

A hybrid electric turboprop includes a propeller, a thermal engine, an electric motor, a gearbox, and an air inlet. The propeller is configured to rotate about a propeller axis and includes a plurality of blades extending radially outwardly from the propeller axis such that, as the propeller is rotated about the propeller axis, the plurality of blades define a substantially circular blade path area centered about the propeller axis and having a radius. The gearbox couples both the thermal engine and the electric motor to the propeller to enable each of the thermal engine and the electric motor to drive rotation of the propeller about the propeller axis. The air inlet defines an opening. A radial distance is defined from the propeller axis to a location within the opening. The radial distance is equal to or less than 60% of the radius.

Air inlet configurations for hybrid aircraft

A screen for an aeronautical gas turbine engine includes a plurality of first filaments and a plurality of second filaments. The plurality of second filaments define a plurality of openings with the plurality of first filaments. The plurality of first filaments and the plurality of second filaments define a first arrangement in which the plurality of first filaments are perpendicular to the plurality of second filaments. Upon application of a force to the screen, at least some of the plurality of first filaments and at least some of the plurality of second filaments are configured to translate from the first arrangement to a second arrangement in which a size of at least one of the openings is configured to change from a first size to a second size.

Turbine engine screen

A fan assembly is provided for a gas turbine engine including: a plurality of fan blades, the plurality of fan blades including a first fan blade; and an actuation assembly including: a first linkage connected to the first fan blade; a first pivot point rotatable with the first fan blade, the first linkage further connected to the first pivot point; a control point moveable relative to the first pivot point and connected to the first linkage for changing a relative position of the first fan blade within the plurality of fan blades.

Actuation assembly for a fan of a gas turbine engine

An apparatus for providing foreign object debris protection an air intake of an aircraft engine. The apparatus includes a frame and a plurality of cross-members. The cross-members are positioned in the frame to define a plurality of screen openings. At least one of the cross-members has an aerodynamically efficient cross section.

Inlet screen for aircraft engines

A bell-mouth scoop assembly includes an actuator comprising a plurality of hinge members configured to rotate in unison about a respective hinge axis of rotation from a first stowed position to a second deployed position and at least one linkage arm extending outwardly from at least one of the plurality of hinge members. The bell-mouth scoop assembly further comprises a bell-mouth panel comprising a panel longitudinal centerline and pivotably coupled to each linkage arm, in the first stowed position the bell-mouth panel (configured to conform to an outer surface of the with the panel longitudinal centerline aligned about a circumference of the flow discharge nozzle, in the second deployed position the bell-mouth panel configured to extend away from the outer surface of the flow discharge nozzle with the longitudinal centerline aligned parallelly with the nozzle centerline.

Method and system for a stowable bell-mouth scoop

A gas turbine engine that includes a nozzle assembly that has features that facilitate airflow into and through a bypass passage of the gas turbine engine during a reverse thrust operation is provided. The nozzle assembly of the gas turbine engine also includes features that increase the effectiveness of the thrust reverse system of the gas turbine engine. Methods for reversing the thrust of a gas turbine engine are also provided.

Bellmouth nozzle assembly for a gas turbine engine

A compression inner core cowl for a jet engine can have a concave annular section of the core cowl. The concave section can begin within the expanse of an outer fan cowl and extend aft of the fan cowl toward the tail cone, defining an annular bypass section between the fan cowling and the core cowling. The concave geometry of the core cowling reduces the strength of supersonic shock waves generated at the corners of the cowlings adjacent a supersonic airflow stream to increase overall efficiency of the engine.

Growing community of inventors

Mazowieckie, Poland

Tomasz Iglewski