COOLED WALL OF A TURBINE COMPONENT AND A METHOD FOR COOLING THIS WALL

A cooled wall of a turbine component includes a first layer of channels for a coolant arranged along a side of the wall facing to a flow of hot gas, the first layer of channels having a serpentine shape, each channel of the first layer having an inlet and an outlet; a second layer of channels for th...

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Bibliographische Detailangaben
Hauptverfasser:	NARYZHNY Oleg, PLODISTYY Maxim, SEDLOV Andrey
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE 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:	A cooled wall of a turbine component includes a first layer of channels for a coolant arranged along a side of the wall facing to a flow of hot gas, the first layer of channels having a serpentine shape, each channel of the first layer having an inlet and an outlet; a second layer of channels for the coolant disposed further from the flow of hot gas than the first layer, each channel of the second layer having an inlet and an outlet, the outlet of each of the channels of the first layer being in fluid communication with corresponding inlet of associated channel of the second layer creating a bend for changing a direction of the coolant leaving the channel of the first layer when entering the channel of the second layer.