Rotor blade system of turbine engines
A rotor blade system. The rotor blade system includes a rotor and a plurality of blades coupled to the rotor. The plurality of blades are arranged in an airfoil distribution pattern. The airfoil distribution pattern includes one or more baseline blades and one or more intentionally mistuned blades including an intentional mistuning feature.
1. A rotor blade system comprising:
a rotor; and
a plurality of blades coupled to the rotor, the plurality of blades arranged in an airfoil distribution pattern, the airfoil distribution pattern comprising one or more baseline blades and one or more intentionally mistuned blades having a first side and a second side opposite the first side, the one or more intentionally mistuned blades including an intentional mistuning feature that includes an under-platform damper positioned under a platform of the one or more intentionally mistuned blades and positioned only on the first side of the one or more intentionally mistuned blades.
2. The rotor blade system of claim 1 , wherein the one or more baseline blades include at least one of a baseline shape, a baseline size, or baseline features, and the intentional mistuning feature is different than the at least one of the baseline shape, the baseline size, or the baseline features of the one or more baseline blades.
3. The rotor blade system of claim 1 , wherein the airfoil distribution pattern is selected from the group consisting of: AB, AAB, or a combination thereof, wherein A is a baseline blade and B is an intentionally mistuned blade.
4. The rotor blade system of claim 1 , wherein the intentional mistuning feature is a first intentional mistuning feature and the one or more intentionally mistuned blades include a second intentional mistuning feature that is selected from the group consisting of:
a reduced chord length from a trailing edge in a tip region of the one or more intentionally mistuned blades relative to a chord length of the one or more baseline blades,
at least one of a varied spanwise location of an internal cavity of the one or more intentionally mistuned blades relative to a spanwise location of an internal cavity of the one or more baseline blades, a varied chordwise location of the internal cavity of the one or more intentionally mistuned blades relative to a chordwise location of the internal cavity of the one or more baseline blades, a varied radial height of the internal cavity of the one or more intentionally mistuned blades relative to a radial height of the internal cavity of the one or more baseline blades, or a varied axial length of the internal cavity of the one or more intentionally mistuned blades relative to an axial length of the internal cavity of the one or more baseline blades,
a mass in the internal cavity of the one or more intentionally mistuned blades,
a powder material in the internal cavity of the one or more intentionally mistuned blades,
a tuned impact damper in the internal cavity of the one or more intentionally mistuned blades,
a friction damper in the internal cavity of the one or more intentionally mistuned blades,
at least one of a varied chord length of a sheath of the one or more intentionally mistuned blades relative to a chord length of a sheath of the one or more baseline blades or a varied thickness of the sheath of the one or more intentionally mistuned blades relative to a thickness of the sheath of the one or more baseline blades,
one or more shock control bumps on the one or more intentionally mistuned blades, or
combinations thereof.
5. The rotor blade system of claim 1 , wherein the first side is a suction side of the one or more intentionally mistuned blades, and the second side is a pressure side of the one or more intentionally mistuned blades.
6. The rotor blade system of claim 1 , wherein the first side is a pressure side of the one or more intentionally mistuned blades, and the second side is a suction side of the one or more intentionally mistuned blades.
7. The rotor blade system of claim 1 , wherein the one or more intentionally mistuned blades include a dovetail having a groove, and the under-platform damper is mounted in the groove.
8. The rotor blade system of claim 1 , wherein the one or more intentionally mistuned blades do not include the under-platform damper on the second side of the one or more intentionally mistuned blades.
9. The rotor blade system of claim 8 , wherein the one or more baseline blades have a first side and a second side, and the one or more baseline blades that are positioned on the first side of the one or more intentionally mistuned blades contact the under-platform damper on the second side of the one or more baseline blades.
10. The rotor blade system of claim 9 , wherein the one or more baseline blades that are positioned on the second side of the one or more intentionally mistuned blades do not contact the under-platform damper on the first side of the one or more baseline blades.
11. A turbine engine comprising:
a fan section;
a compressor section; and
a turbine section, wherein at least one of the fan section, the compressor section, and the turbine section includes a rotor blade system comprising:
a rotor; and
a plurality of blades coupled to the rotor, the plurality of blades arranged in an airfoil distribution pattern, the airfoil distribution pattern comprising one or more baseline blades and one or more intentionally mistuned blades having a first side and a second side opposite the first side, the one or more intentionally mistuned blades including an intentional mistuning feature that includes an under-platform damper positioned under a platform of the one or more intentionally mistuned blades and positioned only on the first side of the one or more intentionally mistuned blades.
12. The turbine engine of claim 11 , wherein the one or more baseline blades include at least one of a baseline shape, a baseline size, or baseline features, and the intentional mistuning feature is different than the at least one of the baseline shape, the baseline size, or the baseline features of the one or more baseline blades.
13. The turbine engine of claim 11 , wherein the airfoil distribution pattern is selected from the group consisting of: AB, AAB, or a combination thereof, wherein A is a baseline blade and B is an intentionally mistuned blade.
14. The turbine engine of claim 11 , wherein the intentional mistuning feature is a first intentional mistuning feature and the one or more intentionally mistuned blades include a second intentional mistuning feature that is selected from the group consisting of:
a reduced chord length from a trailing edge in a tip region of the one or more intentionally mistuned blades relative to a chord length of the one or more baseline blades,
at least one of a varied spanwise location of an internal cavity of the one or more intentionally mistuned blades relative to a spanwise location of an internal cavity of the one or more baseline blades, a varied chordwise location of the internal cavity of the one or more intentionally mistuned blades relative to a chordwise location of the internal cavity of the one or more baseline blades, a varied radial height of the internal cavity of the one or more intentionally mistuned blades relative to a radial height of the internal cavity of the one or more baseline blades, or a varied axial length of the internal cavity of the one or more intentionally mistuned blades relative to an axial length of the internal cavity of the one or more baseline blades,
a mass in the internal cavity of the one or more intentionally mistuned blades,
a powder material in the internal cavity of the one or more intentionally mistuned blades,
a tuned impact damper in the internal cavity of the one or more intentionally mistuned blades,
a friction damper in the internal cavity of the one or more intentionally mistuned blades,
at least one of a varied chord length of a sheath of the one or more intentionally mistuned blades relative to a chord length of a sheath of the one or more baseline blades or a varied thickness of the sheath of the one or more intentionally mistuned blades relative to a thickness of the sheath of the one or more baseline blades,
one or more shock control bumps on the one or more intentionally mistuned blades, or
combinations thereof.
15. The turbine engine of claim 11 , wherein the first side is a suction side of the one or more intentionally mistuned blades, and the second side is a pressure side of the one or more intentionally mistuned blades.
16. The turbine engine of claim 11 , wherein the first side is a pressure side of the one or more intentionally mistuned blades, and the second side is a suction side of the one or more intentionally mistuned blades.
17. The turbine engine of claim 11 , wherein the one or more intentionally mistuned blades include a dovetail having a groove, and the under-platform damper is mounted in the groove.
18. The turbine engine of claim 11 , wherein the one or more intentionally mistuned blades do not include the under-platform damper on the second side of the one or more intentionally mistuned blades.
19. The turbine engine of claim 18 , wherein the one or more baseline blades have a first side and a second side, and the one or more baseline blades that are positioned on the first side of the one or more intentionally mistuned blades contact the under-platform damper on the second side of the one or more baseline blades.
20. The turbine engine of claim 19 , wherein the one or more baseline blades that are positioned on the second side of the one or more intentionally mistuned blades do not contact the under-platform damper on the first side of the one or more baseline blades.