Methods and systems for generating power and thermal management having combined cycle architecture

A system for generating power from at least one heat source associated with a flight vehicle traveling at a flight speed of at least Mach 3, the system comprising:

• a first fluid loop containing a first working fluid, the first fluid loop including, in sequence:
• a first compressor for compressing the first working fluid;
• a first heat intake, located in thermally coupled relation to the at least one heat source associated with the flight vehicle, for heating the first working fluid;
• and
• a first thermal engine for expanding the first working fluid and generating a first work output;
• and
• a second fluid loop containing a second working fluid, the second fluid loop including, in sequence:
• a fluid pressure increasing device for pressurizing the second working fluid;
• a second thermal engine for expanding the second working fluid and generating a second work output;
• a recuperator for exchanging heat from a low pressure leg of the first fluid loop, located between the first thermal engine and the first compressor, to a high pressure leg of the second fluid loop, located between the fluid pressure increasing device and the second thermal engine;
• and
• a heat sink heat exchanger operably coupled to a low pressure leg located in the second fluid loop between the second thermal engine and the fluid pressure increasing device.

A system for generating power from at least one heat source associated with a flight vehicle traveling at a flight speed of at least Mach 3, the system comprising:

• a first fluid loop containing a first working fluid, the first fluid loop including, in sequence:
• a first compressor for compressing the first working fluid;
• a first heat intake, located in thermally coupled relation to the at least one heat source associated with the flight vehicle, for heating the first working fluid;
• and
• a first thermal engine for expanding the first working fluid and generating a first work output;
• and
• a second fluid loop containing a second working fluid, the second fluid loop including, in sequence:
• a fluid pressure increasing device for pressurizing the second working fluid;
• a second thermal engine for expanding the second working fluid and generating a second work output;
• a recuperator for exchanging heat from a low pressure leg of the first fluid loop, located between the first thermal engine and the first compressor, to a high pressure leg of the second fluid loop, located between the fluid pressure increasing device and the second thermal engine;
• and
• a heat sink heat exchanger operably coupled to a low pressure leg located in the second fluid loop between the second thermal engine and the fluid pressure increasing device;
• a first generator operably coupled to the first thermal engine and configured to receive at least a portion of the first work output and generate a first source of electrical power;
• a second generator operably coupled to the second thermal engine and configured to receive at least a portion of the second work output and generate a second source of electrical power;
• and
• a controller operably coupled to the first compressor and the fluid pressure increasing device, wherein the controller is programmed to execute a method, comprising initiating operation of the first compressor and the fluid pressure increasing device when a flight speed of the flight vehicle is above Mach 3.