TEARDROP FILM COOLING BLADE

PROBLEM TO BE SOLVED: To provide a turbine rotor blade for a gas turbine engine. SOLUTION: The turbine blade 10 includes a blade part 12 having an internal cooling circuit 30. The cooling circuit is arranged right behind a front edge 22 and has a first flow path 34 followed by a second flow path 36...

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Bibliographische Detailangaben
Hauptverfasser:	SCHMID SCOTT JOSEPH, KUMAR GANESH NAGAB, NORTON BRAIN ALAN, HEEG ROBERT JOHN
Format:	Patent
Sprache:	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:	PROBLEM TO BE SOLVED: To provide a turbine rotor blade for a gas turbine engine. SOLUTION: The turbine blade 10 includes a blade part 12 having an internal cooling circuit 30. The cooling circuit is arranged right behind a front edge 22 and has a first flow path 34 followed by a second flow path 36 separated therefrom with a corresponding bridge 38. The bridge 38 includes a train of impingement openings 40 for cooling the front edge. A negative pressure side wall 20 of the blade part includes a train of first diffusion film cooling holes 42 extending in the state of passing therethrough along the flow of the first flow path 34. The first holes 42 each have a complex inclination with a rectangular cross section forming an approximately teardrop shaped outlet 46 in a protruded contour of the negative pressure side wall. COPYRIGHT: (C)2005,JPO&NCIPI