Gas turbine engine airfoil frequency design
A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506±10% Hz, a second mode with a frequency of 1732±10% Hz, a third mode with a frequency of 2268±10% Hz, a fourth mode with a frequency of 4007±10% Hz, a fifth mode with a frequency of 4851±10% Hz and a sixth mode with a frequency of 6416±10% Hz.
1. A turbomachine airfoil element comprising:
an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm);
a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 1.52-1.82 inch (38.6-46.2 mm); and
at least two of:
a first mode has a frequency of 506 up to ±10% Hz;
a second mode has a frequency of 1732 up to ±10% Hz;
a third mode has a frequency of 2268 up to ±10% Hz;
a fourth mode has a frequency of 4007 up to ±10% Hz;
a fifth mode has a frequency of 4851 up to ±10% Hz; and
a sixth mode has a frequency of 6416 up to ±10% Hz;
wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode.
2. The element of claim 1 , wherein three of the first, second, third, fourth, fifth and sixth mode frequencies are present.
3. The element of claim 1 , wherein the first mode is a 1EB mode, the second mode is a 1T mode, the third mode is a 2EB mode, the fourth mode is a 2T mode, the fifth mode is a 3EB mode, and the sixth mode is a CWB.
4. The element of claim 3 , wherein the 1EB, 2EB and 3EB modes correspond to deflections substantially parallel to thickness direction, the CWB mode corresponds to bending that is substantially normal to the thickness direction and substantially along the chordwise direction, and the 1T and 2T modes corresponds to twisting about the radial direction.
5. The element of claim 1 , wherein at a running speed/condition:
the first mode has a frequency of 643 up to ±10% Hz;
the second mode has a frequency of 1800 up to ±10% Hz;
the third mode has a frequency of 2367 up to ±10% Hz;
the fourth mode has a frequency of 4070 up to ±10% Hz;
the fifth mode has a frequency of 4801 up to ±10% Hz; and
the sixth mode has a frequency of 6402 up to ±10% Hz.
6. The element of claim 1 , wherein the frequencies are within up to ±5% ranges.
7. The element of claim 1 , wherein the airfoil element is part of an integrally bladed rotor.
8. The element of claim 1 , wherein the airfoil is a titanium-based alloy.
9. The element of claim 8 , the titanium-based alloy has a density of about 0.16 lb/in 3 (4.4 g/cm 3 ).
10. The element of claim 8 , the titanium-based alloy has a modulus of elasticity of about 16-17 Mpsi (110-117 GPa) at room temperature.
11. A method of repairing an airfoil comprising the steps of:
providing an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm), and a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 1.52-1.82 inch (38.6-46.2 mm), wherein the provided airfoil has at least one unrestored mode frequency that is attributable to damage to the airfoil; and
repairing the airfoil to provide at least two of:
a first mode has a frequency of 506 up to ±10% Hz;
a second mode has a frequency of 1732 up to ±10% Hz;
a third mode has a frequency of 2268 up to ±10% Hz;
a fourth mode has a frequency of 4007 up to ±10% Hz;
a fifth mode has a frequency of 4851 up to ±10% Hz; and
a sixth mode has a frequency of 6416 up to ±10% Hz;
wherein 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, wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode.
12. The method according to claim 11 , wherein the first mode is a 1EB mode, the second mode is a 1T mode, the third mode is a 2EB mode, the fourth mode is a 2T mode, the fifth mode is a 3EB mode, and the sixth mode is a CWB, and wherein the airfoil is a titanium-based alloy.
13. A turbofan engine comprising:
a fan section;
a compressor section arranged fluidly downstream from the fan section;
a turbine section arranged fluidly downstream from the compressor section;
a combustor arranged fluidly between the compressor and turbine sections; and
an airfoil in at least one of the fan, compressor and turbine sections, the airfoil having:
pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm);
a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 1.52-1.82 inch (38.6-46.2 mm); and
at least two of:
a first mode has a frequency of 506 up to ±10% Hz;
a second mode has a frequency of 1732 up to ±10% Hz;
a third mode has a frequency of 2268 up to ±10% Hz;
a fourth mode has a frequency of 4007 up to ±10% Hz;
a fifth mode has a frequency of 4851 up to ±10% Hz; and
a sixth mode has a frequency of 6416 up to ±10% Hz;
wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode.
14. The engine of claim 13 , wherein the airfoil is provided in the compressor section.
15. The engine of claim 14 , wherein the compressor section includes a low pressure compressor fluidly upstream from a high pressure compressor, and the airfoil is in the low pressure compressor.
16. The engine of claim 15 , wherein the airfoil element is part of a blade, and the blade is an integrally bladed rotor.
17. The engine of claim 16 , wherein the low pressure compressor includes two stages.
18. The engine of claim 16 , wherein the airfoil is a titanium-based alloy with a density of about 0.16 lb/in 3 (4.4 g/cm 3 ) and with a modulus of elasticity of about 16-17 Mpsi (110-117 GPa) at room temperature.
19. The engine of claim 16 , wherein the first mode is a 1EB mode, the second mode is a 1T mode, the third mode is a 2EB mode, the fourth mode is a 2T mode, the fifth mode is a 3EB mode, and the sixth mode is a CWB, wherein the 1EB, 2EB and 3EB modes correspond to deflections substantially parallel to thickness direction, the CWB mode corresponds to bending that is substantially normal to the thickness direction and substantially along the chordwise direction, and the 1T and 2T modes corresponds to twisting about the radial direction.