| 摘要 |
<p>A turbine blade airfoil (48) has pairs of air flow jet-producing orifices (44) formed through chordwise spaced transverse walls (46) extending between opposite side walls (50,52) of the airfoil and dividing a hollow chamber of the airfoil into a series of separate cavities (38). The pairs of orifices in first (46A,46B) and second (46C,46D,46E) pluralities of the transverse walls direct air flow in opposite directions from intermediate ones of the cavities toward leading (56) and trailing (62) edges of the airfoil. The pairs of orifices (44) in the first plurality of transverse walls (46A,46B) have pairs of axes (54A,54B)that diverge from one another in the direction of cooling air flow toward the leading edge (56) of the airfoil to cause successive impingement against portions of the opposite side walls (50,52) of successive cavities (38A,38B) of a first series of cavities by cooling air flow before exiting from the airfoil through exit holes (60) in the airfoil leading edge (56). The pairs of orifices (44) in the second plurality of transverse walls (46C,46D,46E) have pairs of axes (54C,54D,54E) that diverse from one another in the direction of cooling air flow toward the trailing edge (62) of the airfoil to cause successive impingement against portions of the opposite side walls (50,52) of successive cavities (38D,38E,38F) of a second series of cavities by cooling air flow before exiting from the airfoil through exit holes (64) in the airfoil trailing edge (62). <IMAGE></p> |
