TURBINE AIRFOIL TRAILING EDGE COOLING SLOTS

A turbine airfoil (12) includes pressure and suction sidewalls (42, 44) extending along a span (S) from a base (34) to a tip (36). Spanwise spaced apart trailing edge cooling holes (30) in the pressure sidewall (42) end at corresponding spanwise spaced apart trailing edge cooling slots (66) extendin...

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Bibliographische Detailangaben
Hauptverfasser:	BERGHOLZ, ROBERT FREDERICK, JR, DURSTOCK, DANIEL LEE
Format:	Patent
Sprache:	eng ; fre
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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Zusammenfassung:	A turbine airfoil (12) includes pressure and suction sidewalls (42, 44) extending along a span (S) from a base (34) to a tip (36). Spanwise spaced apart trailing edge cooling holes (30) in the pressure sidewall (42) end at corresponding spanwise spaced apart trailing edge cooling slots (66) extending chordally substantially to the trailing edge (TE). Each cooling hole (30) includes in downstream serial cooling flow relationship, a curved inlet (70), a constant area and constant width metering section (100), and a spanwise diverging section (102) leading into the trailing edge cooling slot (66), and a spanwise height (H) substantially greater than a hole width (W) through the cooling hole (30). A pressure sidewall surface (39) of the pressure sidewall (42) may be planar through the metering and diverging sections (100, 102). The width (W) may be constant through the metering and diverging sections (100, 102). A raised floor (88) may include a flat up ramp (90) in the diverging section (102), a flat down ramp (94) in the slot (66).