Tapered tip-rib turbine blade
AssigneeGeneral Electric Company
InventorsJeffrey C. Mayer, Gary C. Liotta, John H. Starkweather, Antonio C. Gominho
Life of this patent
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Abstract
A gas turbine engine rotor blade 18 includes a dovetail 22 and integral airfoil 24. The airfoil includes a pair of sidewalls 28,30 extending between leading and trailing edges 32,34, and longitudinally between a root 36 and tip 38. The sidewalls are spaced laterally apart to define a flow channel 40 for channeling cooling air through the airfoil. The tip includes a floor 48 atop the flow channel, and a pair of ribs 50,52 laterally offset from respective sidewalls. The ribs are longitudinally tapered for increasing cooling conduction thereof.
Claims18
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 being spaced laterally apart to define a flow channel for channeling cooling air through said airfoil;
- and
- said tip includes a floor atop said flow channel, a first rib laterally offset from said first sidewall atop said floor, and a second rib laterally offset from second sidewall atop said floor, and said ribs being longitudinally tapered to converse outwardly from said tip floor, and laterally offset from said sidewalls to define respective shelves thereatop.
A turbine airfoil comprising first and second laterally spaced apart sidewalls extending between leading and trailing edges, and including a tip having a floor extending between said sidewalls and a pair of tapered ribs extending between said leading and trailing edges laterally offset from said sidewalls to define respective shelves therealong, and each of said ribs converges outwardly from said tip floor.
Dependencies are inferred from the claim text.