Flow channel for a gaseous medium and corresponding exhaust-gas liner of a gas turbine

The invention refers to a flow channel for a gaseous medium, especially a hot exhaust gas of a gas turbine, with improved aerodynamic characteristics. In such a flow channel, a constructionally simple and effective reduction of unwanted flow separations is achieved, even in the event of changing flo...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	RAUCH, MARC, STEFFEN, TOBIAS
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOWOF GASES OR LIQUIDS FLUID-PRESSURE ACTUATORS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS HYDRAULICS OR PNEUMATICS IN GENERAL JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The invention refers to a flow channel for a gaseous medium, especially a hot exhaust gas of a gas turbine, with improved aerodynamic characteristics. In such a flow channel, a constructionally simple and effective reduction of unwanted flow separations is achieved, even in the event of changing flow parameters, by its flow-guiding contours (12, 14, 17) being equipped with an array of dimples (18). A flow channel and an exhaust-gas liner of a gas turbine are provided.