公开(公告)号：US20230043809A1

公开(公告)日：2023-02-09

申请号：US17388618

申请日：2021-07-29

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Jeffrey Douglas Rambo ,  Daniel Alan Niergarth ,  Daniel Lawrence Tweedt ,  Michael Simonetti ,  Michael Julian Castillo ,  Timothy Richard DePuy ,  Steven Benjamin Morris

IPC: F01N3/02 ,  F02C3/04

Abstract: A gas turbine engine is provided including a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a rotor assembly driven by the turbomachine, the rotor assembly, the turbomachine, or both comprising a substantially annular duct relative to the centerline of the gas turbine engine, the annular duct defining a flowpath; a heat exchanger positioned within the annular duct and extending substantially continuously along the circumferential direction, the heat exchanger comprising a first material defining a heat exchange surface exposed to the flowpath, wherein the first material defines a heat exchange coefficient and wherein the heat exchange surface defines a surface area (A), and wherein the heat exchanger has an effective transmission loss (ETL) of between 5 decibels and 1 decibel for an operating condition.