A vane assembly comprises circumferentially adjacent airfoils formed of composite materials. The airfoils have matching exterior geometries defined by pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section. An inner pl
A vane assembly comprises circumferentially adjacent airfoils formed of composite materials. The airfoils have matching exterior geometries defined by pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section. An inner platform is attached to each of the circumferentially adjacent airfoils at the root section, and an outer platform is attached at the tip section. The composite materials are selected to define a vibration mode with different vibration frequencies in the circumferentially adjacent airfoils, where the different vibration frequencies are separated by more than a full width of the vibration mode at half maximum.
대표청구항▼
1. A vane assembly comprising: circumferentially adjacent airfoils formed of composite materials, the circumferentially adjacent airfoils having matching exterior geometries defined by pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root sec
1. A vane assembly comprising: circumferentially adjacent airfoils formed of composite materials, the circumferentially adjacent airfoils having matching exterior geometries defined by pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section;an inner platform attached to each of the circumferentially adjacent airfoils at the root section; andan outer platform attached to each of circumferentially adjacent airfoils at the tip section;wherein the composite materials are selected to define a vibration mode with different vibration frequencies in the circumferentially adjacent airfoils, the different vibration frequencies separated by more than a full width of the vibration mode at half maximum. 2. The vane assembly of claim 1, wherein the vibration mode comprises a fundamental mode of vibration, the fundamental mode having the different vibration frequencies in the circumferentially adjacent airfoils. 3. The vane assembly of claim 1, wherein the vibration mode comprises a higher-order mode of vibration, the higher-order mode having the different vibration frequencies in the circumferentially adjacent airfoils. 4. The vane assembly of claim 1, wherein the matching exterior geometries define substantially identical pressure surfaces and substantially identical suction surfaces for each of the circumferentially adjacent airfoils. 5. The vane assembly of claim 1, wherein the inner and outer platforms are formed as unitary structures attached to each of the circumferentially adjacent airfoils to define a multi-pack stator vane assembly. 6. The vane assembly of claim 5, wherein the circumferentially adjacent airfoils consist of two circumferentially adjacent airfoils defining a twin-pack stator vane assembly. 7. The vane assembly of claim 1, wherein the composite materials of the circumferentially adjacent airfoils comprise organic matrix materials selected to define different densities for the circumferentially adjacent airfoils, as a function of span height. 8. The vane assembly of claim 1, wherein the composite materials of the circumferentially adjacent airfoils comprise fiber materials selected to define different elasticities for the circumferentially adjacent airfoils, as a function of span height. 9. A stator stage comprising a plurality of vane assemblies as specified in claim 1, the plurality of vane assemblies circumferentially arranged about an axis to define a flow duct. 10. A gas turbine engine comprising the stator stage of claim 9. 11. A stator vane assembly comprising: first and second circumferentially adjacent airfoils with matching exterior geometries defined by pressure and suction surfaces extending from a leading edge to a trailing edge and from a root section to a tip section, the first airfoil formed of organic matrix composite materials defining a first vibration response and the second airfoil formed of organic matrix composite materials defining a second vibration response;inner and outer platforms attached to each of the first and second airfoils at the root section and at the tip section, the inner and outer platforms defining a flow duct therebetween;wherein the first and second vibration responses define different fundamental mode frequencies for the first and second airfoils, the fundamental mode frequencies separated by more than a full width at half maximum. 12. The stator vane assembly of claim 11, wherein the matching exterior geometries define substantially identical load characteristics for the first and second circumferentially adjacent airfoils. 13. The stator vane assembly of claim 11, wherein the first and second vibration responses define different higher-order mode frequencies for the first and second airfoils, the higher-order mode frequencies separated by more than a full width at half maximum. 14. The stator vane assembly of claim 13, wherein the organic matrix composite materials have different densities in the first and second airfoils, the different densities selected to differentiate the higher-order mode frequencies in the first and second airfoils. 15. The stator vane assembly of claim 14, wherein the organic matrix composite materials have different elasticities in the first and second airfoils, the different elasticities selected to differentiate the higher-order mode frequencies in the first and second airfoils. 16. A stator vane stage comprising: first and second circumferentially adjacent airfoils formed of organic matrix composite materials, the first and second airfoils having substantially identical external geometries defined by pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section;an inner platform attached to the first and second airfoils at the root section; andan outer platform attached to the first and second airfoils at the tip section, the inner and outer platforms forming a flow duct therebetween;wherein the organic matrix composite materials define different vibration responses in the first and second airfoils, the different vibration responses having vibration modes with different vibration frequencies in the first and second airfoils, the different vibration frequencies separated by more than a full width of the vibration modes at half maximum. 17. The stator vane stage of claim 16, wherein the vibration modes comprise a fundamental mode and a second-order mode or a third-order mode, each of the modes having different vibration frequencies in the first and second airfoils. 18. The stator vane stage of claim 16, wherein the organic matrix composite materials comprise different organic matrix and fiber materials in the first and second airfoils. 19. The stator vane stage of claim 18, wherein the external geometries of the first and second airfoils define circumferentially adjacent airfoils with substantially identical turning and loading characteristics. 20. A turbofan engine comprising a power core and the stator vane stage of claim 16, wherein the stator vane stage is coaxially disposed about the power core in a fan duct.
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