General Electric Company

Michael Vadnais

Ramana Reddy Kollam

Kevin Edward Hinderliter

James Fitzgerald Bonar

Michael John Simonetti

Ryan St Pierre

Nishita Deshmukh

Prerna Mandal

Mehmet Kilic

A gas turbine engine is provided. The gas turbine engine includes: a thermal management system having a thermal fluid member having a flow of thermal fluid therethrough during operation of the gas turbine engine and a heat exchanger assembly, the heat exchanger assembly including: a core section comprising a plurality of heat exchange members; and a heat exchange manifold including a first direction pressure vessel in fluid communication with the thermal fluid member and a second direction pressure vessel extending from the first direction pressure vessel, the first and second direction pressure vessels each extending in a reference plane, the second direction pressure vessel in fluid communication with the first direction pressure vessel and with at least one of the plurality of heat exchange members.

Thermal management system

A gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath. The gas turbine engine also includes a turbine rear frame extending through the core air flowpath at a location downstream of the turbine section and defining a leading edge within the core air flowpath. The gas turbine engine also includes a waste heat recovery system operable to separate, at or upstream of the leading edge of the turbine rear frame, a core airflow exiting the turbine section into a primary exhaust airflow and a waste heat recovery airflow. The waste heat recovery system comprises a heat source exchanger positioned to receive the waste heat recovery airflow.

Waste heat recovery system

Growing community of inventors

Milwaukee, WI, United States of America

Michael Vadnais