초록 ▼

A conformal seal (20) for sealing air flow between a cooling airflow path and a hot gas flow path within a combustion turbine engine. The conformal seal (20) may be fitted within cooperating side slots of adjacent vane segments (10) within the combustion turbine engine. The conformal seal (20) may i

A conformal seal (20) for sealing air flow between a cooling airflow path and a hot gas flow path within a combustion turbine engine. The conformal seal (20) may be fitted within cooperating side slots of adjacent vane segments (10) within the combustion turbine engine. The conformal seal (20) may include an elongated metallic substrate (22, 40) forming an upper surface and a lower surface. A conformal coating (26, 44) may be deposited over one or both surfaces of the substrate (22, 40). The conformal coating (26, 44) may be deposited to a depth so that a point contact between the conformal coating (26, 44) and respective interior walls of the side slots wears the conformal coating (26, 44) to establish surface area contact there between. The surface area contact improves a sealing function between the conformal coating (26, 44) and the respective interior walls during operation of the combustion turbine engine.

대표청구항 ▼

I claim as my invention: 1. An apparatus for sealing air flow between a cooling air flow path and a hot gas flow path within a combustion turbine engine, the apparatus fitted within cooperating side slots of adjacent vane segments within the combustion turbine engine, the apparatus comprising: an e

I claim as my invention: 1. An apparatus for sealing air flow between a cooling air flow path and a hot gas flow path within a combustion turbine engine, the apparatus fitted within cooperating side slots of adjacent vane segments within the combustion turbine engine, the apparatus comprising: an elongated metallic substrate forming an upper surface and a lower surface; and a conformal coating deposited over a portion of at least one of the upper surface and the lower surface, the conformal coating deposited to a depth so that a point contact between the conformal coating and respective interior walls of the side slots wears the conformal coating to establish surface area contact to improve a sealing function between the conformal coating and the respective interior walls during operation of the combustion turbine engine. 2. The apparatus of claim 1 further comprising: a metal coating deposited over the portion of at least one of the upper surface and the lower surface; and the conformal coating deposited on top of the metal coating. 3. The apparatus of claim 2 further comprising the conformal coating comprising a porosity of between about 15%-35% pore volume. 4. The apparatus of claim 3 further comprising the conformal coating comprising a quantity of a fugitive material suitable for forming the porosity of approximately 15%-35% pore volume. 5. The apparatus of claim 1 further comprising the elongated metallic substrate including a pair of longitudinally extending protrusions wherein the conformal coating is deposited between the pair of longitudinally extending protrusions. 6. The apparatus of claim 5 further comprising the conformal coating deposited to cover at least a portion of an upper surface of at least one of the pair of longitudinally extending protrusions. 7. The apparatus of claim 5 further comprising the conformal coating deposited between the pair of longitudinally extending protrusions so that an upper surface of the conformal coating is substantially flush with a respective upper surface of at least one of the pair of longitudinally extending protrusions. 8. The apparatus of claim 7 further comprising the conformal coating comprising a porosity of approximately 15%-35% pore volume. 9. The apparatus of claim 8 further comprising the conformal coating comprising a quantity of a fugitive material suitable to form the porosity of approximately 25% pore volume. 10. The apparatus of claim 1 further comprising the conformal coating comprising a layer of MCrAlY containing hexagonal boron nitride and polyester. 11. A seal for positioning between a pair of adjacent vane segments subjected to vibrational movement during operation of a combustion turbine engine, the seal comprising: a metallic substrate formed to be inserted between the pair of adjacent vane segments; a first layer of MCrAlY having a first density deposited on at least one surface of the metallic substrate; and a second layer of MCrAlY having a second density deposited on the first layer of MCrAlY, wherein the first density is greater than the second density. 12. The seal of claim 11 further comprising the first density being about 95% or greater and the second density being between about 65%-85%. 13. The seal of claim 11 further comprising the second layer of MCrAlY comprising CoNiCrAlY, a quantity of hexagonal boron nitride and a quantity of polyester material deposited on the first layer of MCrAlY so that the second layer of MCrAlY has a pore volume of between about 15%-35%. 14. The seal of claim 11 further comprising the first layer of MCrAlY and the second layer of MCrAlY deposited to a thickness so that an interior wall portion of at least one of the pair of adjacent vane segments engages the second layer of MCrAlY in response to vibrational movement during operation of the combustion turbine engine to establish surface area contact between the second layer of MCrAlY and the interior wall portion to improve a sealing function there between. 15. The seal of claim 14 further comprising the metallic substrate forming a dog bone configuration for fitting within respective side slots of the pair of adjacent vane segments within the combustion turbine engine. 16. A seal for use between adjacent vane segments in a combustion turbine engine, the seal comprising: a substrate; and at least one layer of an abradable material deposited on at least one surface of the substrate, the at least one layer deposited to a depth so that a point contact between the at least one layer and respective interior walls of the adjacent vane segments wears the at least one layer to establish surface area contact there between to improve a sealing function between the at least one layer and the respective interior walls during operation of the combustion turbine engine. 17. The seal of claim 16, the at least one layer of abradable material comprising: a first layer of MCrAlY having a first density deposited on at least one surface of the substrate; and a second layer of MCrAlY having a second density deposited over the first layer of MCrAlY, wherein the first density is greater than the second density. 18. The seal of claim 17 further comprising the first density being about 95% or greater and the second density being between about 65%-85%. 19. The seal of claim 16 further comprising the substrate sized to fit within cooperating side slots of the adjacent vane segments and including a pair of longitudinally extending protrusions wherein the at least one layer is deposited at least between the pair of longitudinally extending protrusions. 20. The seal of claim 16 further comprising the substrate being substantially rectangular and sized to fit within cooperating side slots of the adjacent vane segments and the at least one layer deposited on an upper surface and a lower surface of the substrate.