Method and apparatus for gas turbine engines
A method of assembling a gas turbine engine includes providing at least one blade assembly. The method also includes forming at least one blade tip fuse within at least a portion of the at least one blade assembly. The method further includes coupling the at least one blade assembly into the gas turbine engine. The blade assembly includes an airfoil and a metal leading edge (MLE) coupled to at least a portion of the airfoil. The MLE includes the at least one blade tip fuse.
1. A method of assembling a gas turbine engine, said method comprises:
providing at least one blade assembly;
coupling at least a portion of a metal leading edge (MLE) to at least an airfoil portion of the blade assembly;
forming at least one blade tip fuse within at least a portion of the at least one blade assembly using at least one hinge mechanism within a portion of the MLE, wherein a first portion of the MLE is formed with a first tangential stiffness and a second portion of the MLE is formed with a second tangential stiffness that is less than the first tangential stiffness; and
coupling the at least one blade assembly into the gas turbine engine.
2. A method in accordance with claim 1 wherein forming a second portion of the MLE with a second tangential stiffness comprises at least one of:
forming a notch in at least a portion of the MLE;
deforming at least a portion of the MLE;
thinning a portion of the MLE; and
varying the size of at least a portion of the MLE.
3. A method in accordance with claim 1 wherein forming at least one blade tip fuse further comprises forming the at least one blade tip fuse to deform when subjected to a predetermined load.
4. A method in accordance with claim 3 wherein providing at least one blade assembly comprises further providing at least one blade assembly fabricated from a material that erodes when subjected to a predetermined load.
5. A method in accordance with claim 1 wherein coupling the at least one blade assembly into the gas turbine engine comprises coupling the at least one blade assembly within the gas turbine engine to facilitate mitigating gas turbine engine imbalances.
6. A blade assembly comprising:
an airfoil; and
a metal leading edge (MLE) coupled to at least a portion of said airfoil, said MLE comprises at least one blade tip fuse wherein a first portion of the MLE is formed with a first tangential stiffness and a second portion of the MLE is formed with a second tangential stiffness that is less than the first tangential stiffness.
7. A blade assembly in accordance with claim 6 wherein said MLE is configured to deform when said blade assembly is subjected to a predetermined load.
8. A blade assembly in accordance with claim 7 wherein said MLE further comprises at least one hinge mechanism configured to facilitate deformation of said MLE when said blade assembly is subjected to a predetermined load.
9. A blade assembly in accordance with claim 6 wherein said MLE comprises at least one of:
a solid nose region; and
at least one sidewall.
10. A blade assembly in accordance with claim 6 wherein said airfoil is configured to erode at a predetermined rate when subjected to a predetermined load.
11. A blade assembly in accordance with claim 6 wherein said blade assembly is configured for insertion into a rotating machine, said blade assembly is further configured to mitigate imbalances within the rotating machine.
12. A gas turbine engine comprising:
a rotor;
a casing at least partially extending about said rotor; and
at least one blade assembly coupled to said rotor, said at least one blade assembly comprises:
an airfoil; and
a metal leading edge (MLE) coupled to at least a portion of said airfoil, said MLE comprises at least one blade tip fuse wherein a first portion of the MLE is formed with a first tangential stiffness and a second portion of the MLE is formed with a second tangential stiffness that is less than the first tangential stiffness.
13. A gas turbine engine in accordance with claim 12 wherein said MLE is configured to deform when said blade assembly is subjected to a predetermined load.
14. A gas turbine engine in accordance with claim 13 wherein said MLE further comprises at least one hinge mechanism configured to facilitate deformation of said MLE when said blade assembly is subjected to a predetermined load.
15. A gas turbine engine in accordance with claim 12 wherein said MLE comprises at least one of:
a solid nose region; and
at least one sidewall.
16. A gas turbine engine in accordance with claim 12 wherein said airfoil is configured to erode at a predetermined rate when subjected to a predetermined load.
17. A gas turbine engine in accordance with claim 12 said blade assembly is configured for insertion into a rotating machine, said blade assembly is further configured to mitigate imbalances within the rotating machine.