Turbomachine blade
A turbomachine airfoil element comprises 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 end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400±10% Hz; a second mode resonance frequency is 4950±10% Hz; a third mode resonance frequency is 7800±10% Hz; a fourth mode resonance frequency is 8700±10% Hz; and a fifth mode resonance frequency is 12500±10% Hz.
1. A combination of a turbomachine blade and a turbine disk or fixture in which the blade is mounted, the blade formed of a nickel-based superalloy and comprising:
a platform having an outboard surface and an underside;
an inboard attachment root extending from the platform underside and mounted in the turbine disk or fixture;
an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side, the inboard end at the platform outboard surface and the outboard end being a free tip,
wherein:
at 70° F. the nickel-based superalloy is a single crystal alloy having a density of 0.315-0.330 pounds per cubic inch and a modulus of elasticity of 17.5-18.5E06 psi;
a span of the airfoil between the inboard end and the outboard end is 1.75-2.20 inches;
a chord length at 50% of the span is 1.05-1.35 inches; and
at a zero speed and ambient conditions:
a first mode resonance frequency is 2400±10% Hz;
a second mode resonance frequency is 4950±10% Hz;
a third mode resonance frequency is 7800±10% Hz;
a fourth mode resonance frequency is 8700±10% Hz; and
a fifth mode resonance frequency is 12500±10% Hz.
2. The combination of claim 1 wherein the blade is mounted in said disk in a gas turbine engine wherein, at a running speed/condition:
the first mode resonance frequency is 2210±10% Hz;
the second mode resonance frequency is 4810±10% Hz;
the third mode resonance frequency is 7600±10% Hz;
the fourth mode resonance frequency is 8400±10% Hz; and
the fifth mode resonance frequency is 12000±10% Hz.
3. The combination of claim 1 , wherein the blade is a casting.
4. The combination of claim 1 further comprising: a cooling passageway system in the airfoil.
5. The combination of claim 4 wherein the cooling passageway system comprises: one or more inlets; and one or more outlets.
6. The combination of claim 1 wherein: said first mode resonance frequency is 2400+5% Hz; said second mode resonance frequency is 4950+5% Hz; said third mode resonance frequency is 7600+5% Hz; said fourth mode resonance frequency is 8400 5% Hz; and said fifth mode resonance frequency is 12500 5% Hz.
7. A turbine engine comprising a turbomachine airfoil element being a blade mounted in a disk of the turbine engine, the blade formed of a nickel-based superalloy and comprising:
a platform having an outboard surface and an underside;
an inboard attachment root extending from the platform underside and mounted in the disk;
an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side, the inboard end at the platform outboard surface and the outboard end being a free tip,
wherein:
at 70° F. the nickel-based superalloy is a single crystal alloy having a density of 0.315-0.330 pounds per cubic inch and a modulus of elasticity of 17.5-18.5E06 psi;
a span of the airfoil between the inboard end and the outboard end is 1.75-2.20 inches;
a chord length at 50% of the span is 1.05-1.35 inches; and
at a running speed/condition:
a first mode resonance frequency is 2210±10% Hz;
a second mode resonance frequency is 4810±10% Hz;
a third mode resonance frequency is 7600±10% Hz;
a fourth mode resonance frequency is 8400±10% Hz; and
a fifth mode resonance frequency is 12000±10% Hz.
8. A turbine engine comprising a turbomachine airfoil element being a blade mounted in a disk of the turbine engine, the blade formed of a nickel-based superalloy and comprising:
a platform having an outboard surface and an underside;
an inboard attachment root extending from the platform underside and mounted in the disk;
an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side, the inboard end at the platform outboard surface and the outboard end being a free tip,
wherein:
at 70° F. the nickel-based superalloy is a single crystal alloy having a density of 0.315-0.330 pounds per cubic inch and a modulus of elasticity of 17.5-18.5E06 psi;
a span of the airfoil between the inboard end and the outboard end is 1.75-2.20 inches;
a chord length at 50% of the span is 1.05-1.35 inches; and
in a running condition:
a first mode resonance frequency is 2175±10% Hz;
a second mode resonance frequency is 4500±10% Hz;
a third mode resonance frequency is 7100±10% Hz;
a fourth mode resonance frequency is 7800±10% Hz; and
a fifth mode resonance frequency is 11150±10% Hz.
9. A method for remanufacturing a turbine engine airfoil element, the turbine engine airfoil element being a blade formed of a nickel-based superalloy and comprising:
a platform having an outboard surface and an underside;
an inboard attachment root extending from the platform underside;
an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side, the inboard end at the platform outboard surface and the outboard end being a free tip, the method comprising providing:
a first mode resonance frequency is 2400±10% Hz;
a second mode resonance frequency is 4950±10% Hz;
a third mode resonance frequency is 7800±10% Hz;
a fourth mode resonance frequency is 8700±10% Hz; and
a fifth mode resonance frequency is 12500±10% Hz,
wherein the providing comprises addition of superalloy and said first, second, third, fourth, and fifth mode frequencies are measured with the blade in a turbine engine disk or disk-simulating fixture.
10. The method of claim 9 wherein the providing comprises removal of material after the addition.
11. The method of claim 9 wherein the providing comprises measuring a frequency response after the addition and thereafter further modifying the airfoil via removing or adding superalloy.
12. The method of claim 9 wherein:
the provided airfoil element has at least one unrestored mode frequency that is attributable to damage to the airfoil element; and
at least one of the first mode frequency, second mode frequency, third mode frequency, fourth mode frequency, and fifth mode frequency corresponds to a restored mode frequency that supersedes the unrestored mode frequency.
13. The method of claim 9 further comprising:
applying a thermal barrier coating over the added superalloy.