GAS TURBINE BLADE

PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of reducing pressure loss by reducing a separating region at a film cooling air inlet portion, reducing power of a cooling air supply source, and further improving film cooling efficiency.SOLUTION: A conical inlet portion is disposed at an...

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Bibliographische Detailangaben
Hauptverfasser:	MIYOSHI ICHIRO, MORISAKI TETSURO
Format:	Patent
Sprache:	eng
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 provide a gas turbine blade capable of reducing pressure loss by reducing a separating region at a film cooling air inlet portion, reducing power of a cooling air supply source, and further improving film cooling efficiency.SOLUTION: A conical inlet portion is disposed at an inlet side of high pressure, of a film cooling hole. The conical shape is defined to have a bottom surface on a wall surface at a high pressure side, of a film cooling hole disposed, for example, on an aerofoil portion of a gas turbine blade, and an end wall portion at an outer peripheral side or an inner peripheral side of the aerofoil portion, to guide cooling air, and to guide the cooling air to a surface of the aerofoil portion and the like.