Reverse cavity blade for a gas turbine engine
A rotor blade for a turbine engine includes an airfoil section which extends from a platform section opposite a root section, the airfoil section defines a cavity which extends from an airfoil tip section toward a root section.
1. A rotor blade for a turbine engine comprising:
a platform section;
a root section which extends from said platform section; and
an airfoil section which extends from said platform section opposite said root section, said airfoil section defines a cavity which extends from an airfoil tip section toward said root section, wherein said root section is solid, and wherein said airfoil tip section receives a cover plate to close said cavity.
2. The rotor blade as recited in claim 1 , wherein said cavity decreases toward said root section.
3. The rotor blade as recited in claim 1 , wherein said cavity extends from a leading edge to a trailing edge at said airfoil tip section.
4. The rotor blade as recited in claim 1 , wherein said airfoil section defines a positive taper ratio.
5. The rotor blade as recited in claim 1 , wherein said rotor blade is a low pressure turbine blade.
6. The rotor blade as recited in claim 1 , further comprising a rail which extends from said cover plate.
7. The rotor blade as recited in claim 6 , wherein a first rail and a second rail extend from respective first and second platforms of said airfoil tip section, said first rail radially offset from said second rail, said first platform radially offset from said second platform.
8. The rotor blade as recited in claim 1 , wherein said cover plate completely closes said cavity.
9. A method of forming a rotor blade comprising:
defining a cavity which extends from an airfoil tip section toward a root section of an airfoil section of a turbine blade, wherein said root section solid, and wherein said airfoil tip section receives a cover plate to close said cavity.
10. The method as recited in claim 9 , further comprising:
defining a wall thickness about the cavity with respect to a minimum material manufacturing limit.
11. The method as recited in claim 9 , further comprising:
defining a wall thickness about the cavity with respect to a maximum stress allowable limit.
12. The method as recited in claim 9 , further comprising:
defining a wall thickness about the cavity with respect to a minimum material manufacturing limit or maximum stress allowable limit, whichever is less.
13. The method as recited in claim 9 , wherein said cover plate completely closes said cavity.
14. A rotor blade for a turbine engine comprising:
a platform section;
a root section which extends from said platform section; and
an airfoil section which extends from said platform section opposite said root section, said airfoil section defines a cavity which extends from an airfoil tip section toward said root section, wherein said airfoil tip section receives a cover plate to close said cavity;
wherein a first rail and a second rail extend from respective first and second platforms of said airfoil tip section, said first rail radially offset from said second rail, said first platform radially offset from said second platform; and
wherein said cover plate is provided between said first rail and said second rail to cover an opening in said first and second platforms, and to completely close said cavity.
15. The rotor blade as recited in claim 14 , wherein said cover plate is substantially Z-shaped.