Low cooling flow turbine blade
A turbine rotor blade made from a spar and a shell each having an airfoil cross sectional shape and each formed from a high temperature exotic material and formed by a wire EDM process to form a thin wall shell from Molybdenum and the spar from Waspalloy or IN100 in order to form a turbine blade that requires very low amounts of cooling air while allowing for high temperature use above what nickel super alloys can be exposed to. The spar and shell are secured to the platform by a bolt passing through the widest section of the hollow spar and connected at one end to a tip cap and to the other end to the platform and root piece of the blade.
1. A turbine blade for a gas turbine engine comprising:
a platform and root;
a thin wall shell having an airfoil cross sectional shape with a leading edge and a trailing edge, and a pressure side wall and a suction side wall extending between the two edges;
a spar having an airfoil cross sectional shape with a leading edge and a trailing edge, and a pressure side wall and a suction side wall extending between the two edges;
a tip cap to secure the shell to the spar;
the tip cap includes a conical shaped transition extending toward the platform and shaped to spread a stress load around sides of the tip cap; and,
the conical shaped transition has an upper end that extends from a leading edge of the tip cap to a trailing edge of the tip cap within a space formed within the shell.
2. A turbine blade for a gas turbine engine comprising:
a platform and root;
a thin wall shell having an airfoil cross sectional shape with a leading edge and a trailing edge, and a pressure side wall and a suction side wall extending between the two edges;
a spar having an airfoil cross sectional shape with a leading edge and a trailing edge, and a pressure side wall and a suction side wall extending between the two edges;
a tip cap to secure the shell to the spar; and,
the tip cap includes a conical shaped transition extending toward the platform and shaped to spread a stress load around sides of the tip cap;
the tip cap includes a threaded hole facing the platform; and,
a bolt passing through the root and platform screws into the threaded hole to secure the spar and shell to the platform.
3. The turbine blade of claim 1 , and further comprising:
the tip cap includes a bolt extension extending from the conical shaped transition;
the root and platform includes a hole passing through to receive the bolt extension; and,
a threaded nut screwed onto the bolt extension to secure the spar and shell to the platform.
4. The turbine blade of claim 1 , and further comprising:
the shell and the spar are formed by a wire EDM process.
5. The turbine blade of claim 1 , and further comprising:
the shell is Molybdenum.
6. The turbine blade of claim 1 , and further comprising:
the spar is made from Waspalloy or IN100.
7. The turbine blade of claim 1 , and further comprising:
the tip cap and conical transition is a single piece and made from Molybdenum.
8. The turbine blade of claim 2 , and further comprising:
the bolt is made from MP159.
9. The turbine blade of claim 1 , and further comprising:
the shell is a thin wall shell made from Molybdenum.
10. The turbine blade of claim 1 , and further comprising:
the tip cap and conical transition is a single crystal material.
11. The turbine blade of claim 1 , and further comprising:
the tip cap and conical transition is a directional solidified material.
12. The turbine blade of claim 1 , and further comprising:
a bolt or bolt extension passing through a leading edge region of the spar to secure the shell between the tip cap.
13. The turbine blade of claim 1 , and further comprising:
the tip cap includes a threaded hole facing the platform; and,
the threaded hole is closer to a leading edge side of the blade tip than a trailing edge side.
14. A tip cap for a turbine rotor blade having a spar and shell construction with the tip cap secured to the spar to secure the shell between the tip cap, the tip cap comprising:
a leading edge side and a trailing edge side;
a pressure side and a suction wall side both extending between the leading edge and the trailing edge;
an underside of the tip cap forming an abutment surface for a top end of the shell;
a conical shaped transition piece extending from a lower side of the tip cap;
a fastener hole opening on a bottom end of the conical shaped transition piece;
the fastener hole located closer to the leading edge than the trailing edge of the tip cap; and,
the conical shaped transition has an upper end that extends from a leading edge of the tip cap to a trailing edge of the tip cap within a space formed within the shell.
15. The tip cap of claim 14 , and further comprising:
the fastener hole opening is adjacent to a widest section of the tip cap.
16. A turbine blade for a gas turbine engine comprising:
a platform and root;
a thin wall shell having an airfoil cross sectional shape with a leading edge and a trailing edge, and a pressure side wall and a suction side wall extending between the two edges;
a spar having an airfoil cross sectional shape with a leading edge and a trailing edge, and a pressure side wall and a suction side wall extending between the two edges;
a tip cap separate from the spar;
a threaded bolt to secure the shell and the spar between the tip cap and the platform with the spar being located within the shell;
the tip cap includes a threaded hole facing the platform; and,
a bolt passing through the root and platform screws into the threaded hole to secure the spar and shell to the platform.
17. The turbine blade of claim 16 , and further comprising:
the tip cap includes a conical shaped transition extending toward the platform shaped to spread a stress load around sides of the tip cap.