Methods and systems for generating power and thermal management having dual loop architecture
AssigneeThe Boeing Company
InventorsMichael F. Stoia, Joseph S. Silkey, Jacob T. Needels, Kevin G. Bowcutt
Life of this patent
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Abstract
Methods and apparatus for power generation and/or thermal management on a high speed flight vehicle include circulating a power generation loop working fluid through a power generation loop, which absorbs heat associated with the flight vehicle. A generator operably coupled to the power generation loop generates electrical power. Additionally, a heat transport loop working fluid may circulate through a heat transport loop to provide thermal management through heat transfer.
Claims20
A system for providing cooling and/or generating power on board a flight vehicle using heated inlet air associated with the 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;
- an inlet air heat exchanger, the inlet air heat exchanger including an inlet air line fluidly communicating with the heated inlet air, and a first air-to-loop line receiving the first working fluid and located in thermally coupled relation to the inlet air line;
- a first thermal engine for expanding the first working fluid and generating a first work output;
- a second fluid loop containing a second working fluid, the second fluid loop including, in sequence:
- a second compressor for compressing the second working fluid;
- the inlet air heat exchanger, the inlet air heat exchanger including a second air-to-loop line receiving the second working fluid and located in thermally coupled relation to the inlet air line;
- and
- a second thermal engine for expanding the second working fluid and generating a second work output.
A system for providing cooling and generating power on board a flight vehicle using heated inlet air associated with the flight vehicle traveling at a flight speed of at least Mach 3, the system comprising:
- a power generation loop containing a power generation loop working fluid, the power generation loop including, in sequence:
- a power generation loop compressor for compressing the power generation loop working fluid;
- an inlet air heat exchanger, the inlet air heat exchanger including an inlet air line fluidly communicating with the heated inlet air, and a first air-to-loop line receiving the power generation loop working fluid and located in thermally coupled relation to the inlet air line;
- and
- a power generation loop thermal engine for expanding the power generation loop working fluid and generating a power generation loop work output;
- a heat transport loop containing a heat transport loop working fluid, the heat transport loop including, in sequence:
- a heat transport loop compressor for compressing the heat transport loop working fluid;
- the inlet air heat exchanger, the inlet air heat exchanger including a second air-to-loop line receiving the heat transport loop working fluid and located in thermally coupled relation to the inlet air line;
- and
- a heat transport loop thermal engine for expanding the heat transport loop working fluid and generating a heat transport work output, wherein the heat transport work output is mechanically coupled to the heat transport loop compressor;
- a generator operably coupled to the power generation loop thermal engine and configured to receive at least a portion of the power generation loop work output and generate auxiliary electrical power;
- and
- a controller operably coupled to the power generation loop compressor and the heat transport loop compressor, wherein the controller is programmed to execute a method, comprising initiating operation of the power generation loop compressor and the heat transport loop compressor when a flight speed of the flight vehicle is above Mach 3.
A system for providing cooling and/or generating power on board a flight vehicle using heated inlet air associated with the 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 configured to compress the first working fluid;
- an inlet air heat exchanger, the inlet air heat exchanger comprising:
- an inlet air line configured to fluidly communicate with the heated inlet air, and
- a first air-to-loop line configured to receive the first working fluid and configured to receive heat from the inlet air line and increase a temperature of the first working fluid;
- and
- a first thermal engine configured to expand the first working fluid and generate a first work output;
- a second fluid loop containing a second working fluid, the second fluid loop including, in sequence:
- a second compressor configured to compress the second working fluid;
- the inlet air heat exchanger, the inlet air heat exchanger comprising a second air-to-loop line configured to receive the second working fluid and configured to receive heat from the inlet air line and increase a temperature of the second working fluid;
- and
- a second thermal engine configured to expand the second working fluid and generate a second work output.
Dependencies are inferred from the claim text.