초록 ▼

This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade

This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade tips. The abradable coating system includes columns of an abradable material. Thus, interference between the blades and the abradable coating system causes the individual columns to break off at the base. This abrasion mechanism may reduce blade wear and spalling of the coating system when compared to conventional coatings.

대표청구항 ▼

I claim: 1. An abradable coating system for turbine airfoils, comprising: an outer surface of a turbine component; a forming matrix supported on the outer surface of the turbine component, wherein the forming matrix is formed from a plurality of walls that are coupled together to form a plurality o

I claim: 1. An abradable coating system for turbine airfoils, comprising: an outer surface of a turbine component; a forming matrix supported on the outer surface of the turbine component, wherein the forming matrix is formed from a plurality of walls that are coupled together to form a plurality of cells having at least one opening opposite the outer surface; and a first abradable coating deposited in the plurality of cells, wherein the forming matrix is formed from a material that melts during operation of a turbine engine in which the coating system is positioned thereby leaving the first abradable coating attached to the turbine component and forming a plurality of columns separated by voids. 2. The abradable coating system of claim 1, further comprising a second coating deposited between said outer surface of a turbine component and said first abradable coating such that said forming matrix is attached to an outer surface of the second coating. 3. The abradable coating system of claim 2, wherein said second coating is selected from the group consisting of a thermal barrier coating and a bond coating. 4. The abradable coating system of claim 3, further comprising a bond coating deposited on said outer surface and wherein said second coating is a thermal barrier coating and is deposited on said bond coating. 5. The abradable coating system of claim 1, wherein said turbine component is a ring seal segment positioned radially outward from the tips of rotatable turbine blades. 6. The abradable coating system of claim 1, wherein said material forming the forming matrix is a fugitive material selected from the group consisting of plastics and molybdenum. 7. The abradable coating system of claim 1, wherein said forming matrix is formed from walls having a thickness of less than about 0.5 mils and 5 mils. 8. The abradable coating system of claim 1, wherein each of the cells of the plurality of cells has a cross-sectional area in a plane generally aligned with the outer surface of the turbine component that is less than about 2 mm2. 9. The abradable coating system of claim 1, wherein said first abradable coating is selected from the group consisting of 8YSZ and ceria stabilized zirconia. 10. The abradable coating system of claim 1, wherein at least one cell of the plurality of cells forming the forming matrix has a cross-sectional shape that is selected from the group consisting of a circle, an ellipse, a triangle, a rectangle, a hexagon, and a diamond. 11. The abradable coating system of claim 1, further comprising an alarm system for identifying whether a turbine blade tip has contacted the first abradable coating. 12. The abradable coating system of claim 11, wherein the alarm system comprises a metalized layer positioned between an outer surface of the turbine component and a tip of the columns of the abradable coating, wherein the metalized layer is coupled to an alarm system that is usable for actuating an alarm when a tip of a turbine blade contacts the metalized layer indicating the tip has worn through a predetermined distance of the abradable coating. 13. The abradable coating system of claim 1, further comprising a temperature sensor on the first abradable coating. 14. The abradable coating system of claim 13, wherein the temperature sensor is formed from at least two metals. 15. An abradable coating system for turbine airfoils, comprising: an outer surface of a ring seal segment; a forming matrix supported on the outer surface of the ring seal segment, wherein the forming matrix is formed from a plurality of walls that are coupled together to form a plurality of cells having at least one opening opposite the outer surface; and a first abradable coating deposited in the plurality of cells, wherein the forming matrix is formed from a material that melts during operation of a turbine engine in which the coating system is positioned thereby leaving the first abradable coating attached to the turbine component and forming a plurality of columns separated by voids. 16. The abradable coating system of claim 15, further comprising a bond coating deposited between said first abradable coating and said outer surface of a turbine component such that said forming matrix is attached to an outer surface of the second coating. 17. The abradable coating system of claim 15, wherein at least one cell of the plurality of cells forming the forming matrix has a cross-sectional shape that is selected from the group consisting of a circle, an ellipse, a triangle, a rectangle, a hexagon, and a diamond. 18. The abradable coating system of claim 15, further comprising an alarm system comprising a metalized layer positioned between an outer surface of the turbine component and a tip of the columns of the abradable coating wherein the metalized layer is coupled to an alarm system that is usable for actuating an alarm when a tip of a turbine blade contacts the metalized layer indicating the tip has worn through a predetermined distance of the abradable coating. 19. The abradable coating system of claim 15, further comprising a temperature sensor on the first abradable coating.