Twin rib turbine blade
First Claim
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1. A turbine blade comprising an airfoil and integral dovetail for mounting said airfoil to a rotor disk inboard of a turbine shroud, said airfoil including:
- first and second sidewalls joined together at a leading edge and a trailing edge, and extending from a root disposed adjacent said dovetail to a tip plate for channeling thereover combustion gases, and a cooling channel disposed in said airfoil for receiving cooling fluid through said dovetail;
a first tip rib extending outwardly from said tip plate between said leading and trailing edges;
a second tip rib extending outwardly from said tip plate between said leading and trailing edges, and spaced laterally from said first tip rib to define an open-top tip channel having a tip inlet near said leading edge for receiving said combustion gases, and a tip outlet near said trailing edge for discharging said combustion gases; and
each of said first and second tip ribs has an airfoil profile including opposite concave and convex sides extending from said tip inlet to said tip outlet for extracting energy from said combustion gases.
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Abstract
A turbine blade includes an airfoil and integral dovetail. The airfoil includes first and second sidewalls joined together at leading and trailing edges, and extending from a root to a tip plate. Twin ribs extend outwardly from the tip plate between the leading and trailing edges, and are spaced laterally apart to define an open-top tip channel therebetween. Each of the tip ribs has an airfoil profile for extracting energy from combustion gases flowable around the turbine blade.
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Citations
20 Claims
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1. A turbine blade comprising an airfoil and integral dovetail for mounting said airfoil to a rotor disk inboard of a turbine shroud, said airfoil including:
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first and second sidewalls joined together at a leading edge and a trailing edge, and extending from a root disposed adjacent said dovetail to a tip plate for channeling thereover combustion gases, and a cooling channel disposed in said airfoil for receiving cooling fluid through said dovetail; a first tip rib extending outwardly from said tip plate between said leading and trailing edges; a second tip rib extending outwardly from said tip plate between said leading and trailing edges, and spaced laterally from said first tip rib to define an open-top tip channel having a tip inlet near said leading edge for receiving said combustion gases, and a tip outlet near said trailing edge for discharging said combustion gases; and each of said first and second tip ribs has an airfoil profile including opposite concave and convex sides extending from said tip inlet to said tip outlet for extracting energy from said combustion gases. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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- 11. A turbine airfoil comprising first and second sidewalls joined together at a tip plate extending between leading and trailing edges, and a pair of laterally spaced apart tip ribs extending outwardly from said tip plate, with each tip rib having laterally opposite concave and convex sides initiating at forward ends thereof and terminating at opposite aft ends thereof.
- 17. A turbine airfoil comprising twin tip ribs extending chordally between opposite forward and aft ends thereof with aerodynamically conforming lifting profiles.
Specification