General Electric Company

Mra Systems, Inc.

Richard David Cedar

Graham Frank Howarth

Mustafa Dindar

Michael Moses Martinez

Andrew Breeze-Stringfellow

Andrew Michael Roach

Steven Thomas Davies

Darek Tomasz Zatorski

David William Crall

Keith Edward James Blodgett

Patrick John Lonneman

Scott Andrew Burton

Joseph Donofrio

Timothy Richard Depuy

Wendy Wenling Lin

Patrick Michael Marrinan

Nikolai N Pastouchenko

David Patrick Calder

Syed Arif Khalid

Daniel Lawrence Tweedt

Jixian Yao

William Joseph Bowden

Timothy Richard DePuy

Egbert Geertsema

Robert William Davidoff

Rudramuni Kariveerappa Majjigi

David Baker Riddle

Shanmugam Murugappan

Mark Graham Turner

Aleksander Piotr Pasieczny

Adam Wayne Clark

Michael William Siekman

Paul David Orkwis

Keith Edward Blodgett

The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.

Inlet cowl for a turbine engine

An acoustic liner may include an acoustic core having an array of resonant cells, and an acoustic screen disposed across the array of resonant cells. The resonant cells include a plurality of cell walls and a resonant space defined by the plurality of cell walls. The acoustic core may include a folded acoustic core. Additionally, or in the alternative, at least some of the resonant cells may include an oblique polyhedral cellular structure and/or a multitude of sound-attenuating protuberances. The acoustic screen may include a reticulate membrane and a support lattice.

Acoustic liners with enhanced acoustic absorption and reduced drag characteristics

The present disclosure provides acoustic structures and related systems and methods which may be used to dampen or attenuate sound waves, including, for example, noise generated by or emanating from various aspects or components of turbomachines such as turbine engines. These acoustic structures include oblique polyhedral cellular structures, including converging polyhedral cells and diverging polyhedral cells, and related systems and methods of making and using such acoustic structures.

Acoustic liners with oblique cellular structures

An acoustic liner () with perforation () and method of constructing () an acoustic liner including forming perforations in the facing sheet by grit blasting () the facing sheet and mounting () the facing sheet to one side of a support layer having a set of partitioned cavities wherein the facing sheet closes an open face of the cavities except for the perforations to form a set of acoustic resonator cells.

Acoustic liner and methods of constructing an acoustic liner

An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.

Acoustic liners for use in a turbine engine

A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.

Unducted thrust producing system

An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.

Aircraft having an AFT engine

Vane assembly for an unducted thrust producing system

An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.

Acoustic liners and method of shaping an inlet of an acoustic liner

An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.

Immersed core flow inlet between rotor blade and stator vane for an unducted fan gas turbine

Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner section may have cambered or an elliptical axially curved cross-section. Spinner axial cross-section may have longer spinner axial distance compared to baseline axial distance of baseline cross-section and spinner aspect ratio greater than baseline aspect ratio of baseline cross-section.

Crosswind performance aircraft engine spinner

A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.

Exhaust nozzle with non-coplanar and/or non-axisymmetric shape

A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct.

Variable slope exhaust nozzle

A gas turbine engine turbine stage has an annular row of turbine airfoils including a first plurality of first airfoils having a first chord length and a second plurality of second airfoils having a second chord length shorter than the first chord length. At least one of the second airfoils is circumferentially disposed between each adjacent pair of the first airfoils. A second leading edges of the second airfoils are located downstream of first leading edges of the first airfoils. The first and second airfoils have different first and second temperature capabilities respectively and the first temperature capability is greater than the second temperature capability. The first and second airfoils may be made from different alloys and/or the second airfoils may be constructed to use lower amounts of cooling airflow than the first airfoils. More than one of the second airfoils may be disposed between each pair of the first airfoils.

Growing community of inventors

Cincinnati, OH, United States of America

Richard David Cedar