United Technologies Corporation

Raytheon Technologies Corporation

Amr Ali

Steven H Zysman

Constantine Baltas

Nigel David Sawyers-Abbott

Yuan J Qiu

Ryan Edward LeBlanc

Kevin J Cummings

An exemplary geared turbomachine assembly includes an acoustic treatment that is in an unducted area of a geared turbomachine.

Acoustic treatment in an unducted area of a geared turbomachine

A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. The outer nacelle is secured to an inner portion through a mount flange at a first axial location. An acoustic treatment extends inwardly of the outer portion of the nacelle and across the axial location of the mount flange and further inwardly toward the fan blades.

Gas turbine engine with one piece acoustic treatment

A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan. A nozzle associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

Variable fan nozzle using shape memory material

An example acoustic treatment for a geared turbomachine establishes a portion of the core cowl aft the fan cowl.

Acoustic treatment in geared turbomachine

A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.

Reduced height ligaments to minimize non-integral vibrations in rotor blades

A gas turbine engine () includes a fan (), a nacelle () arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage () downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow () from the fan. A nozzle () associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

A liner assembly for an aircraft engine housing includes a noise attenuation structure that is covered by a face sheet. The face sheet covering the noise attenuation structure includes a surface having a plurality of circumferentially spaced apart acoustic energy absorption areas that are interspersed between a corresponding plurality of acoustic energy reflective areas. The acoustic energy reflective areas scatter higher order acoustic modes into a plurality of lower order modes. The difficult to attenuate lower order acoustic modes produced by the various acoustic energy cancel each other out to provide significant improvement in liner noise reduction efficiency.

Multi-splice acoustic liner

A propfan assembly includes a plurality of blades that each include an internal cavity containing a noise attenuation structure. Acoustic energy is communicated to the internal cavity through a plurality of openings in the blade surfaces. The cavities include features for attenuating noise energy to reduce generation of noise emitted from the propfan assembly.

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South Windsor, CT, United States of America

Amr Ali