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. At least three of the following resonance frequencies are present. 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. A fifth mode resonance frequency is 14808.2±10% Hz.
1. A turbomachine airfoil element comprising:
an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side,
wherein:
a span between the inboard end and the outboard end is 1.4-1.6 inch;
a chord length at 50% span is 0.9-1.4 inch; and
at least three 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 element of claim 1 wherein: all of said first, second, third, fourth, and fifth mode resonance frequencies are present.
3. The element of claim 2 wherein: the first mode is a 1 EB mode; the second mode is a 1 SWB mode; the third mode is a 1 T mode; the fourth mode is a 2 EB mode; and the fifth mode is a 2 T mode.
4. The element of claim 2 wherein: a sixth mode resonance frequency is 16667.5±10% Hz.
5. The element of claim 1 wherein: said resonance frequencies are at zero speed and ambient conditions.
6. The element of claim 5 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.
7. The element of claim 1 being a blade having an inboard attachment root.
8. The blade of claim 7 wherein: the outboard end is a free tip.
9. The element of claim 1 being a casting.
10. The element of claim 1 formed of a nickel-based superalloy.
11. The element of claim 10 further comprising: a cooling passageway system in the airfoil.
12. The element of claim 11 wherein the cooling passageway system comprises: one or more inlets; and one or more outlets.
13. The element of claim 1 wherein:
the first mode resonance frequency is 2591.5±5% Hz;
the second mode resonance frequency is 4675.2±5% Hz;
the third mode resonance frequency is 7892.9±5% Hz;
the fourth mode resonance frequency is 10098.2±5% Hz; and
the fifth mode resonance frequency is 14808.2±5% Hz.
14. An airfoil element for a turbomachine, the airfoil element comprising:
plural cavities, wherein the cavities are cord-wise adjacent, and span-wise extending between opposing leading and trailing edges of the airfoil;
the airfoil having plural modes, including:
one or more easywise bending modes, including at least one of a first easywise bending mode at 2591.5±10% Hz and a second easywise bending mode at 10098.2±10% Hz;
one or more stiffwise bending modes, including a first stiffwise bending mode at 4675.2±10% Hz; and
one or more twist modes, including at least one of a first twist mode occurring at 7892.9±10% Hz and a second twist mode occurring at 14808.2±10% Hz.
15. The airfoil of claim 14 , wherein:
the or more easywise bending modes corresponds to deflections substantially parallel to the airfoil thickness;
the one or more stiffwise bending mode corresponds to bending that is substantially normal to the easywise bending, and substantially along the airfoil chord; and
the one or more twist modes corresponds to twisting about an engine radial axis.
16. The airfoil element of claim 14 , where: the one or more easywise bending modes includes said first and second easywise bending modes.
17. The airfoil element of claim 14 , where: the one or more twist modes includes said first and second twist modes.
18. The airfoil element of claim 14 , where a span between an inboard end of the airfoil and an outboard end of the airfoil is 1.4 to 1.6 inches.
19. The airfoil element of claim 18 , where a chord length, at 50% span, is 0.9 to 1.4 inches.
20. A turbomachine airfoil element comprising:
an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side,
wherein:
a span between the inboard end and the outboard end is 1.4-1.6 inch;
a chord length at 50% span is 0.9-1.4 inches; and
at a running speed/condition at least three of:
a first mode resonance frequency is 2585.4±10% Hz;
a second mode resonance frequency is 4590.1±10% Hz;
a third mode resonance frequency is 7625.9±10% Hz;
a fourth mode resonance frequency is 9848.0±10% Hz; and
a fifth mode resonance frequency is 14385.1±10% Hz.