General Electric Company

Steven B Morris

Jeffrey Douglas Rambo

Scott Alan Schimmels

Timothy Richard DePuy

William Joseph Bowden

Brandon Wayne Miller

Vicente Jerez Fidalgo

Arthur William Sibbach

Trevor Howard Wood

Kishore Ramakrishnan

Nikolai N Pastouchenko

Matthew Thomas Beyer

Victor Moreno Patan

Michael John Simonetti

Eric Barre

Leonardo Aguilar Willys

A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (L), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.

Gas turbine engine having a heat exchanger located in an annular duct

An engine includes a fan section having an open fan defining an axial centerline and a rotor. The rotor includes a plurality of fan blades mounted to a hub and being rotatable about the axial centerline. The engine also includes a turbomachine downstream of the fan section. The turbomachine includes a core cowl that defines an engine inlet and encloses turbomachinery. Further, the engine includes an airflow diverting assembly downstream of the fan section and upstream of the engine inlet. The airflow diverting assembly includes at least one fluid passageway formed into at least a portion of the hub for diverting at least a portion of a boundary layer on a surface of the hub away from the surface of the hub to reduce distortion caused by the boundary layer in the turbomachinery.

Engine having an open fan with reduced boundary layer induced distortion

A gas turbine engine is provided, having a turbomachine and a rotor assembly driven by the turbomachine and operable at a first blade passing frequency (f) greater than or equal to 2,500 hertz and less than or equal to 5,000 hertz during a high power operating condition; a heat exchanger positioned within an annular duct and extending substantially continuously along the circumferential direction, wherein an effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for a high power operating condition, and wherein the heat exchanger comprises a heat transfer section defining an acoustic length (L), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to:

An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.

Gas turbine exhaust nozzle noise abatement

Growing community of inventors

Mason, OH, United States of America

Steven B Morris