Combined structure air film hole for cooling front edge of turbine blade

The utility model discloses a combined structure air film hole for cooling the leading edge of a turbine blade, which comprises a first through hole and a taper hole which are sequentially communicated from the inlet direction to the outlet direction, the first through hole and the taper hole are ar...

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Bibliographische Detailangaben
Hauptverfasser:	ZHOU JIANGFENG, WANG HAILIN, DU ZHINENG, FANG YUAN, CAI PENG, XU SHIHUI, WANG MING
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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 utility model discloses a combined structure air film hole for cooling the leading edge of a turbine blade, which comprises a first through hole and a taper hole which are sequentially communicated from the inlet direction to the outlet direction, the first through hole and the taper hole are arranged in a non-coaxial manner, and the cross sectional area of the outlet of the taper hole is larger than the area of the cross section of the first through hole; the axis of the first through hole is a straight line; and the inner wall surface of the first through hole and the inner wall surface of the conical hole have no corner angles. A good cooling air film can be formed at the front edge of the blade, the first through hole controls the flow of cooling air, the conical hole increases the outlet area of the air film hole, the speed of cooling air at the outlet of the air film hole is reduced, the covering effect of cooling air flow is improved, the cooling effect of the blade is remarkably improved, and the