Tapered tip turbine blade

A gas turbine engine blade comprising:

• a dovetail;
• an airfoil integrally joined to said dovetail, and including first and second sidewalls extending between leading and trailing edges and longitudinally between a root and tip and said sidewalls increased laterally apart to define a flow channel for channeling cooling air through said airfoil;
• and
• said tip includes:
• a slots extending between said leading and trailing edges and facing outwardly;
• a plurality of tip holes extending longitudinally from said flow channel to said slot in flow communication therebetween;
• a laterally outwardly facing first slope extending chordally between said leading and trailing edges, and being longitudinally arcuate between said first sidewall and tip slop to effect a longitudinal taper decreasing in lateral thickness above said first sidewell.

A gas turbine engine blade comprising;

• a dovetail;
• an airfoil integrally joined to said dovetail, and including first and second sidewalls extending between leading and trailing edges and longitudinally between a root and a solid tip, and said sidewalls being spaced laterally apart to define with said tip a flow channel for channel cooling air through said airfoil;
• and
• said tip includes:
• a slot extending between said leading and trailing edges and facing outwardly;
• a plurality of tip holes extending longitudinally form said flow channel to said slot in flow communication therebetween;
• a laterally outwardly facing first slope extending chordally between said leading and trailing edges, and longitudinally between said first sidewall and tip slot;
• and
• a laterally outwardly facing second slope extending chordally between said leading and trailing edges, and longitudinally between said second sidewall and tip slot to collectively affect with said first slope taper of said tip for decreasing lateral thickness thereof longitudinally above said first and second sidewalls to decrease thickness of said tip to said flow channel.