| 摘要 |
Gas turbine engines working on an inverted Brayton cycle (IBC) which provides increased power output at a same fuel flow as is currently used in some other known cycles (e.g., air bottoming cycle) are described. In one embodiment, the engine includes a compressor coupled by a first shaft to a high pressure turbine. A combustor is located in the flow intermediate the compressor and high pressure turbine. A free wheeling power turbine is located downstream of the high pressure turbine, and the power turbine is coupled to a load by a second shaft. The flow from the power turbine is supplied, e.g., via ducts, to an axial turbine coupled to an axial compressor by a third shaft. A heat exchanger is located in the flow intermediate the axial turbine and axial compressor. In operation, the working fluid (e.g., air) is compressed by the compressor, and the compressed air is injected into the combustor which heats the air causing it to expand. The expanded air is forced through the high pressure turbine and the expanded air is supplied to the power turbine. Energy from the power turbine is transferred to the load via the second shaft. At least a portion of the air flow from the power turbine is supplied to the axial turbine which operates as an expander. The expanded air flow is supplied to an inlet of the heat exchanger, where at least a portion of the air flow is cooled from, for example, 600 degrees Fahrenheit to about 89 degrees Fahrenheit. The cooled and expanded air flow is supplied to the compressor, and air from the compressor is discharged into the atmosphere.
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