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US 11,635,023 B1Granted
Multi-spool CO2 aircraft power system for operating multiple generators
AssigneeHamilton Sundstrand Corporation
InventorsStephen H. Taylor, Malcolm P. MacDonald
Life of this patent
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Abstract
A CO2 bottoming cycle system includes a first compressor operatively connected to a first turbine through a first shaft. A first generator is operatively connected to the first shaft. A second compressor is fluidically connected to the first compressor. The second compressor is operatively connected to a second turbine through a second shaft. A second generator is operatively connected to the second shaft. The first turbine is fluidically connected to the second turbine.
Claims20
A CO2 bottoming cycle system using a CO2 working fluid comprising:
- a first compressor operatively connected to a first turbine having a first turbine pressure ratio through a first shaft;
- a first generator operatively connected to the first shaft;
- a second compressor fluidically connected to the first compressor, the second compressor being operatively connected to a second turbine having a second turbine pressure ratio through a second shaft, the second turbine pressure ratio being substantially similar to the first turbine pressure ratio, wherein the second turbine is fluidically connected, in series, to the first turbine;
- and
- a second generator operatively connected to the second shaft, wherein the first turbine is fluidically connected to the second turbine.
2 more elements
An aircraft system comprising:
- a compressor portion;
- a turbine portion operatively connected to the compressor portion through a shaft, the turbine portion including a turbine exhaust;
- a combustor fluidically connecting the compressor portion and the turbine portion;
- and
- a CO2 bottoming cycle using a CO2 working fluid including:
- a first compressor operatively connected to a first turbine having a first turbine pressure ratio through a first shaft;
- a first generator operatively connected to the first shaft;
- a second compressor fluidically connected to the first compressor, the second compressor being operatively connected to a second turbine having a second turbine pressure ratio through a second shaft, the second turbine pressure ratio being substantially similar to the first turbine pressure ratio wherein the second turbine is fluidically connected, in series, to the first turbine;
- a second generator operatively connected to the second shaft, wherein the first turbine is fluidically connected to the second turbine;
- and
- an exhaust heat exchanger in a heat exchange relationship with the turbine exhaust.
8 more elements
Dependencies are inferred from the claim text.