COOLING CIRCUIT FOR MULTI-WALL BLADE

PROBLEM TO BE SOLVED: To reduce pressure loss in a multi-wall turbine blade cooling circuit.SOLUTION: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the t...

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Bibliographische Detailangaben
Hauptverfasser:	CHARLES PERRY JACOB II, WEBER DAVID WAYNE, MEHMET SULEYMAN CIRAY
Format:	Patent
Sprache:	eng ; jpn
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS 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:	PROBLEM TO BE SOLVED: To reduce pressure loss in a multi-wall turbine blade cooling circuit.SOLUTION: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; where the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.SELECTED DRAWING: Figure 1 【課題】多重壁タービンブレード冷却回路の圧力損失を低減させること。【解決手段】一実施形態によるタービンブレード冷却システムは、タービンブレードの第１のチャンネルを通じて流れる第１のガス流をタービンブレードの中央プレナムの中へ向きを変えるための第１のターンと、タービンブレードの第２のチャンネルを通じて流れる第２のガス流を中央プレナムの中へ向きを変えるための第２のターンとを備え、中央プレナムにおける第１のガス流と第２のガス流の衝突を低減するように第１のターンは第２のターンからずれている。【選択図】図１