Turbine rotor blade and aero-engine

The invention relates to the technical field of aero-engines, and discloses a turbine rotor blade and an aero-engine. The turbine rotor blade comprises a blade body and a blade root which are arranged in the radial direction, the blade body comprises a front edge area, a middle chord area and a tail...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	YU LEI, FANG YIHAN
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 invention relates to the technical field of aero-engines, and discloses a turbine rotor blade and an aero-engine. The turbine rotor blade comprises a blade body and a blade root which are arranged in the radial direction, the blade body comprises a front edge area, a middle chord area and a tail edge area which are arranged in the chordwise direction, a first heat exchange cavity is formed in the front edge area, and a second heat exchange cavity extending into the tail edge area is formed in the middle chord area. The first heat exchange cavity and the second heat exchange cavity are separated through a partition plate set. The blade root is provided with a first air inlet communicating with the first heat exchange cavity and a second air inlet communicating with the second heat exchange cavity. Compared with the conventional technology that one path of cold air is used for cooling the whole blade, the turbine rotor blade of the structure uses two paths of cold air, so that the flowing path of each path