General Electric Company

Eric Barre

Brandon Wayne Miller

Jeffrey Douglas Rambo

Victor Moreno Patan

Leonardo Aguilar Willys

Scott Alan Schimmels

Steven Douglas Johnson

John Carl Glessner

Andrew Hudecki

Timothy Richard DePuy

Steven B Morris

Efren Souza Chavez

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

A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.

Gas turbine engine

A thermal management system includes a thermal circuit having a thermal transport bus with a thermal fluid flowing therethrough. The thermal transport bus includes first and second bus segments. First and second thermal loads are on the first and second bus segments, respectively, and have different first and second inlet temperature requirements. The thermal management system includes a plurality of heat exchangers in thermal communication with the first and second thermal loads. The heat exchangers include a first heat exchanger and one or more second heat exchangers. The first heat exchanger is on one of the first or second bus segments for rejecting heat to engine fuel. The thermal fluid is split between each of the first and second bus segments such that only a portion of the thermal fluid flows through the first heat exchanger to accommodate the different first and second inlet temperature requirements.

Thermal management system for an engine

Growing community of inventors

Cincinnati, OH, United States of America

Eric Barre