Thermal management system

A gas turbine engine comprising:

• a compressor section coupled to a turbine section by one or more shafts;
• a main lubrication system for providing lubrication to one or more components located in at least one of the compressor section or the turbine section;
• and
• a thermal management system including
• a thermal transport bus having a heat exchange fluid flowing therethrough;
• a pump for generating a flow of the heat exchange fluid in the thermal transport bus;
• a plurality of heat source exchangers in thermal communication with the heat exchange fluid in the thermal transport bus, the plurality of source exchangers including a main lubrication heat exchanger in thermal communication with the main lubrication system;
• a surface heat exchange module in thermal communication with the heat exchange fluid in the thermal transport bus at a location downstream of the plurality of heat source exchangers for transferring heat from the heat exchange fluid to a surface of one or more components of the gas turbine engine;
• and
• a plurality of heat sink exchangers in thermal communication with the heat exchange fluid in the thermal transport bus for removing heat from the heat exchange fluid in the thermal transport bus, each heat sink exchanger of the plurality of heat sink exchangers selectively in thermal communication with the heat exchange fluid in the thermal transport bus;
• wherein the thermal transport bus is configured as a closed loop system, and wherein the surface heat exchange module is a closed loop module fluidly separate from the thermal transport bus.

A thermal management system for incorporation at least partially into at least one of an aircraft or a propulsion engine of the aircraft, the thermal management system comprising:

• a thermal transport bus having a heat exchange fluid flowing therethrough;
• a pump for generating a flow of the heat exchange fluid in the thermal transport bus;
• a plurality of heat source exchangers in thermal communication with the heat exchange fluid in the thermal transport bus;
• a surface heat exchange module in thermal communication with the heat exchange fluid in the thermal transport bus at a location downstream of the plurality of heat source exchangers for transferring heat from the heat exchange fluid to a surface of one or more components of the propulsion engine or the aircraft;
• and
• a plurality of heat sink exchangers in thermal communication with the heat exchange fluid in the thermal transport bus for removing heat from the heat exchange fluid in the thermal transport bus, each heat sink exchanger of the plurality of heat sink exchangers selectively in thermal communication with the heat exchange fluid in the thermal transport bus;
• wherein the thermal transport bus is configured as a closed loop system, and wherein the surface heat exchange module is a closed loop module, and wherein the surface heat exchange module is configured to transfer heat from the heat exchange fluid flowing through the thermal transport bus to a separate surface heat exchange module fluid.