Turbomachine blade
A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. The element is remanufactured by providing first, second, third, fourth, and fifth mode resonance frequencies respectively of 2591.5±10% Hz, 4675.2±10% Hz, 7892.9±10% Hz, 10098.2±10% Hz, and 14808.2±10% Hz.
1. A method for remanufacturing a turbomachine airfoil element, the element comprising an airfoil having an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side, a span between the inboard and an outboard end being 1.4-1.6 inch, a chord length at 50% span being 0.9-1.4 inch, the method comprising:
receiving a blade in a first condition; and
remanufacturing the blade to a second condition, the remanufacturing providing at least two of:
a first mode resonance frequency is 2591.5±10% Hz;
a second mode resonance frequency is 4675.2±10% Hz;
a third mode resonance frequency is 7892.9±10% Hz;
a fourth mode resonance frequency is 10098.2±10% Hz; and
a fifth mode resonance frequency is 14808.2±10% Hz.
2. The method of claim 1 wherein the manufacturing comprises addition of superalloy.
3. The method of claim 2 wherein the manufacturing comprises removal of material after the addition.
4. The method of claim 2 wherein the manufacturing comprises measuring a frequency response after the addition and thereafter further modifying the airfoil via removing or adding superalloy.
5. The method of claim 2 wherein:
the provided airfoil element has at least one unrestored mode frequency that is attributable to damage to the airfoil element; and
the at least one of the first mode frequency, second mode frequency, third mode frequency, fourth mode frequency, fifth mode frequency, and sixth mode frequency corresponds to a restored mode frequency that supersedes the unrestored mode frequency.
6. The method of claim 2 further comprising:
applying a thermal barrier coating over the added superalloy.
7. The method of claim 6 wherein airfoil element comprises:
a substrate having a density of 0.30-0.34 pounds per cubic inch.
8. The method of claim 1 wherein all of said first, second, third, fourth, and fifth mode resonance frequencies are present.
9. The method of claim 1 wherein: the first mode is a 1EB mode; the second mode is a 1SWB mode; the third mode is a 1T mode; the fourth mode is an 2EB mode; and the fifth mode is a 2T mode.
10. The method of claim 1 wherein: a sixth mode resonance frequency is 16667.5±10% Hz.
11. The method of claim 1 wherein: said resonance frequencies are at zero speed and ambient conditions.
12. The method of claim 1 wherein, at a running speed/condition:
the first mode resonance frequency is 2585.4±10% Hz;
the second mode resonance frequency is 4590.1±10% Hz;
the third mode resonance frequency is 7625.9±10% Hz;
the fourth mode resonance frequency is 9848.0±10% Hz; and
the fifth mode resonance frequency is 14385.1±10% Hz.
13. The method of claim 1 , the element being a blade having an inboard attachment root.
14. The method of claim 13 wherein: the outboard end is a free tip.
15. The method of claim 1 , the element being a casting.
16. The method of claim 1 , the element formed of a nickel-based superalloy.
17. The method of claim 16 , the element further comprising: a cooling passageway system in the airfoil.
18. The method of claim 17 wherein the cooling passageway system comprises:
one or more inlets; and one or more outlets.
19. The method of claim 18 wherein:
the nickel-based superalloy has a density of 0.30-0.34 pounds per cubic inch.
20. The method of claim 1 wherein:
a first mode resonance frequency is 2591.5±5% Hz;
a second mode resonance frequency is 4675.2±5% Hz;
a third mode resonance frequency is 7892.9±5% Hz;
a fourth mode resonance frequency is 10098.2±5% Hz; and
a fifth mode resonance frequency is 14808.2±5% Hz.
21. A method for remanufacturing a turbomachine airfoil element, the element comprising an airfoil having an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side, a span between the inboard and an outboard end being 1.4-1.6 inch, a chord length at 50% span being 0.9-1.4 inch, the method comprising:
addition of superalloy; and
removal of material after the addition, the remanufacturing providing at least two of:
a first mode resonance frequency is 2591.5±10% Hz;
a second mode resonance frequency is 4675.2±10% Hz;
a third mode resonance frequency is 7892.9±10% Hz;
a fourth mode resonance frequency is 10098.2±10% Hz; and
a fifth mode resonance frequency is 14808.2±10% Hz.
22. A method for remanufacturing a turbomachine airfoil element, the element comprising an airfoil having an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side, a span between the inboard and an outboard end being 1.4-1.6 inch, a chord length at 50% span being 0.9-1.4 inch, the method comprising:
addition of superalloy; and
measuring a frequency response after the addition and thereafter further modifying the airfoil via removing or adding superalloy, the remanufacturing providing at least two of:
a first mode resonance frequency is 2591.5±10% Hz;
a second mode resonance frequency is 4675.2±10% Hz;
a third mode resonance frequency is 7892.9±10% Hz;
a fourth mode resonance frequency is 10098.2±10% Hz; and
a fifth mode resonance frequency is 14808.2±10% Hz.