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US 12,366,177 B2Granted
Turbomachine for an aircraft propulsion drive
AssigneeMTU Aero Engines AG
InventorsIstvan Bolgar, Francois Cottier, Milena Fois
Life of this patent
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Abstract
The invention relates to a turbomachine for a flight propulsion drive with a compressor, a combustion chamber, a turbine through which a gas flow flows in the flow direction of turbomachine, and a heat exchanger downstream of the turbine, wherein the heat exchanger is equipped to generate steam from water using energy from the gas flow, which can be supplied with fuel to the gas flow for combustion in the combustion chamber.
Claims6
A turbomachine for an aircraft propulsion drive with a gas flow in a flow direction of the turbomachine through a compressor, comprising:
- a combustion chamber,
- a turbine and
- a heat exchanger downstream of the turbine,
- wherein the heat exchanger is configured and arranged to use energy from the gas flow in the flow direction of the turbomachine from burned fuel in the combustion chamber,
- wherein the heat exchanger has at least two flow channels substantially extending in at least one transfer plane and being parallel to the flow direction of the turbomachine, through which material substantially flows also parallel to the flow direction of the turbomachine, the gas being configured and arranged to flow perpendicularly across the at least two flow channels, in the at least one transfer plane, which are located parallel to the flow direction of the turbomachine, the at least two flow channels of the heat exchanger at least partially radially overlapping the turbine,
- whereby each flow channel is configured and arranged with the at least one transfer plane in the flow direction of the turbomachine equidistant to the turbine.
3 more elements
Dependencies are inferred from the claim text.