General Electric Company

General Electric Company Polska Sp. Z O.o.

Michal Tomasz Kuropatwa

Adam Wojciech Deskiewicz

Nicholas Joseph Kray

Robert Kaminski

Adam Kunicki

Ravindra Shankar Ganiger

John Douglas Mickol

Santosh Kumar Prasad

A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.

Rotor assembly for a gas turbine engine

Compressor bleed slots with variable wall structures are disclosed herein. An example apparatus disclosed herein is to be coupled to a wall of a bleed slot of a compressor of a gas turbine engine, the bleed slot defining a flow path, the apparatus comprising a member to be coupled to the wall, and a plate coupled to the member, the plate having a first geometry at a first ambient condition at a first time, the flow path having a first area when the plate has the first geometry, and a second geometry at a second ambient condition at a second time, the flow path having a second area when the plate has the second geometry, the first area greater than the second area, the first time after the second time.

Compressor bleed slots with variable wall structures

An airfoil assembly for a gas turbine engine includes: an inner support structure configured to circumscribe a longitudinal axis of the gas turbine engine; an outer support structure configured to circumscribe the longitudinal axis of the gas turbine engine, the outer support structure circumscribing the inner support structure; and a stage including a plurality of airfoils extending from the inner support structure towards the outer support structure, the plurality of airfoils including: a first airfoil defining a first sweep angle, a first axial position, and a first lean angle; and a second airfoil defining a second sweep angle, a second axial position, and a second lean angle, wherein the second sweep angle is different than the first sweep angle, the second axial position is different than the first axial position, the second lean angle is different than the first lean angle, or a combination thereof.

Airfoil assembly with a differentially oriented stage

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Warsaw, Poland

Michal Tomasz Kuropatwa