Riblets for a flowpath surface of a turbomachine
A component stage for a turbomachine includes a component section. The component section includes a flowpath surface at least partially exposed to a core air flowpath defined by the turbomachine, when the component stage is installed in the turbomachine. The component further includes a plurality of sequentially arranged riblets on the flowpath surface, the plurality of sequentially arranged riblets customized for an anticipated location of the flowpath surface within the turbomachine by defining one or both of a non-uniform geometry or a non-uniform spacing.
1. A component stage for a turbomachine defining a core air flowpath, the component stage comprising:
a component section, the component section comprising a flowpath surface at least partially exposed to the core air flowpath and further comprising a plurality of sequentially arranged riblets on the flowpath surface, the plurality of sequentially arranged riblets defining one or both of a non-uniform geometry or a non-uniform spacing;
wherein each of the plurality of riblets extend generally in a first direction, wherein each of the plurality of riblets include a top, and wherein the tops of each of the plurality of riblets define a width, and wherein the widths of the tops of the plurality of riblets is non-uniform along the first direction; and
wherein the component section comprises a rotor blade defining a leading edge and a tip, wherein the flowpath surface of the component section comprises a surface of the rotor blade, and wherein the plurality of riblets extend in a non-linear direction from the leading edge towards the tip; and
wherein the rotor blade further defines a pressure side and a suction side, wherein one of the plurality of riblets is on the pressure side.
2. The component stage of claim 1 , wherein each of the plurality of riblets extend generally in a first direction, and wherein each of the plurality of riblets define one or both of a non-uniform geometry or a non-uniform spacing along the first direction.
3. The component stage of claim 1 , wherein the plurality of riblets define a spacing between adjacent riblets, and wherein the spacing defined by the plurality of riblets is non-uniform along the first direction; and
wherein each of the plurality of sequentially arranged riblets are raised features on the flowpath surface.
4. The component stage of claim 1 , wherein the plurality of riblets extend generally in the first direction, and wherein the plurality of riblets define one or both of a non-uniform geometry or a non-uniform spacing in a direction perpendicular to the first direction.
5. The component stage of claim 1 , wherein the component section comprises at least one of a nozzle or a rotor blade, and wherein the flowpath surface of the component section comprises a surface of the nozzle or the rotor blade.
6. The component stage of claim 1 , wherein the component section comprises a base geometry, wherein the base geometry comprises the flowpath surface, wherein the base geometry is formed by casting, and wherein the plurality of riblets are added to the flowpath surface using an additive manufacturing process.
7. A turbomachine comprising:
a compressor section and a turbine section in serial flow order and defining at least in part a core air flowpath, one of the compressor section or the turbine section comprising a component stage, the component stage comprising a component section, the component section comprising a flowpath surface at least partially exposed to the core air flowpath and further comprising a plurality of sequentially arranged riblets on the flowpath surface, the plurality of sequentially arranged riblets defining a non-uniform geometry relative to one another; and
wherein the component section comprises a rotor blade defining a leading edge and a tip, wherein the flowpath surface of the component section comprises a surface of the rotor blade, and wherein the plurality of riblets extend in a non-linear direction from the leading edge towards the tip;
wherein the rotor blade further defines a pressure side and a suction side, wherein one of the plurality of riblets is on the pressure side.
8. The component stage of claim 1 , wherein the tops of each of the plurality of riblets are substantially flat along the first direction; and
wherein each of the plurality of sequentially arranged riblets are raised features on the flowpath surface.
9. The turbomachine of claim 7 , wherein each of the plurality of riblets extend generally in a first direction, wherein the plurality of riblets define a spacing between adjacent riblets, and wherein the spacing defined by the plurality of riblets is non-uniform along the first direction; and
wherein each of the plurality of sequentially arranged riblets are raised features on the flowpath surface.
10. The turbomachine of claim 7 , wherein the plurality of riblets extend generally in a first direction, and wherein the plurality of riblets define one or both of a non-uniform geometry or a non-uniform spacing in a direction perpendicular to the first direction.
11. The turbomachine of claim 7 , wherein the component section comprises at least one of a nozzle or a rotor blade, and wherein the flowpath surface of the component section comprises a surface of the nozzle or the rotor blade.