Closed cycle heat engine for a gas turbine engine

An aeronautical gas turbine engine comprising:

• a turbomachine, wherein the turbomachine defines an axis and a radial direction;
• a closed cycle heat engine defining an axis offset from the axis of the turbomachine along the radial direction of the turbomachine, the closed cycle heat engine comprising
• a compressor configured to compress a working fluid, wherein the working fluid is a supercritical fluid;
• a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid;
• an expander coupled to the compressor for expanding the working fluid;
• and
• an output shaft driven by the expander;
• and
• a means for receiving power from the output shaft of the closed cycle heat engine and providing at least a portion of such power to the turbomachine.

An aeronautical gas turbine engine comprising:

• a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order, wherein the turbine section comprises a low pressure turbine and a high pressure turbine;
• an aeronautical propulsor driven at least in part by the turbomachine;
• and
• a closed cycle heat engine comprising:
• a compressor configured to compress a working fluid;
• a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid, the primary heat exchanger is located within the turbine section of the turbomachine at a location upstream of the low pressure turbine and downstream of the high pressure turbine;
• an expander coupled to the compressor for expanding the working fluid;
• a heat engine shaft extending between the expander and the compressor;
• and
• an output shaft driven by the expander.