초록 ▼

A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further in

A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.

대표청구항 ▼

1. A turbine nozzle assembly comprising: an inner circumferential support platform;an outer circumferential support platform;a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform, wherein each of the plurality of airfo

1. A turbine nozzle assembly comprising: an inner circumferential support platform;an outer circumferential support platform;a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform, wherein each of the plurality of airfoil vanes includes a first, leading end cooling air passageway extending through a central core of each airfoil vane and a second, vane cooling air passageway leading to a vane cooling circuit within each airfoil vane;a plurality of impingement plates comprising cooling impingement holes formed through the plates, the plurality of impingement plates being disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, wherein the impingement plates are physically joined with the outer or inner circumferential support platform along a periphery of the impingement plates, wherein the periphery includes a cut-out edge of the impingement plates adjacent to an opening to the first, leading end cooling air passageway such that no portion of any impingement plate is disposed radially over any portion of the first, leading end cooling air passageway, while wherein each impingement plate is disposed radially over a respective one of the second, vane cooling air passageways; anda plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates, wherein the plurality of gap-maintaining features are disposed within and inward from the periphery including inward from the cut-out edge, and wherein the cooling impingement holes surround all lateral sides of the gap-maintaining features with respect to the surface of the impingement plate,wherein each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates, andwherein each gap-maintaining feature of the plurality of gap-maintaining features is disposed within 1 mm to 5 mm of a respective one of the second, vane cooling air passageways. 2. The turbine nozzle assembly of claim 1, wherein each impingement plate of the plurality of impingement plates comprises a plurality of cooling impingement holes. 3. The turbine nozzle of claim 2, wherein the plurality of gap-maintaining features are disposed within the periphery such that at least one gap-maintaining feature of the plurality of gap-maintaining features is disposed between two of the plurality of impingement holes, and wherein at least one of the two of the plurality of impingement holes is disposed between the cut-out edge of the periphery and the at least one gap-maintaining feature. 4. The turbine nozzle assembly of claim 1, wherein each vane of the plurality of airfoil vanes is disposed along a radially outer surface of the inner circumferential support platform and a radially inner surface of the outer circumferential support platform. 5. The turbine nozzle assembly of claim 4, wherein each vane of the plurality of vanes is disposed opposite each impingement plate of the plurality of impingement plates along opposite radial surfaces of the outer circumferential support platform. 6. The turbine nozzle assembly of claim 1, wherein the outer circumferential support platform comprises a plurality of cooling airflow openings that provide a passageway for cooling air to flow from the air flow space into a cooling circuit of the vane. 7. The turbine nozzle assembly of claim 1, wherein the plurality of gap-maintaining features are formed along an inner radial surface of each impingement plate of the plurality of impingement plates. 8. The turbine nozzle assembly of claim 1, wherein the plurality of gap-maintaining features are formed along an outer radial surface of the outer circumferential support platform. 9. The turbine nozzle assembly of claim 1, wherein the plurality of gap-maintaining features comprise a plurality of hemispherical dimple structures. 10. A method for manufacturing a turbine nozzle assembly comprising the steps of: forming an inner circumferential support platform;forming an outer circumferential support platform;disposing a plurality of airfoil vanes between the inner circumferential support platform and the outer circumferential support platform, wherein each of the plurality of airfoil vanes includes a first, leading end cooling air passageway extending through a central core of each airfoil vane and a second, vane cooling air passageway leading to a vane cooling circuit within each airfoil vane;disposing a plurality of impingement plates comprising cooling impingement holes formed through the plates, the plurality of impingement plates being along a radially outer surface of the outer circumferential support platform or along a radially inner surface of the inner circumferential support platform, wherein the impingement plates are physically joined with the outer or inner circumferential support platform along a periphery of the impingement plates, wherein the periphery includes a cut-out edge of the impingement plates adjacent to an opening to the first, leading end cooling air passageway such that no portion of any impingement plate is disposed radially over any portion of the first, leading end cooling air passageway, while wherein each impingement plate is disposed radially over a respective one of the second, vane cooling air passageways; andproviding a plurality of gap-maintaining features between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates, wherein the plurality of gap-maintaining features are disposed within and inward from the periphery including inward from the cut-out edge, and wherein the cooling impingement holes surround all lateral sides of the gap-maintaining features with respect to the surface of the impingement plate,wherein each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates, andwherein each gap-maintaining feature of the plurality of gap-maintaining features is disposed within 1 mm to 5 mm of a respective one of the second, vane cooling air passageways. 11. The method for manufacturing the turbine nozzle assembly of claim 10, further comprising forming in each impingement plate of the plurality of impingement plates a plurality of cooling impingement holes. 12. The method for manufacturing the turbine nozzle assembly of claim 10, further comprising disposing each vane of the plurality of airfoil vanes along a radially outer surface of the inner circumferential support platform and a radially inner surface of the outer circumferential support platform. 13. The method for manufacturing the turbine nozzle assembly of claim 12, further comprising disposing each vane of the plurality of vanes opposite each impingement plate of the plurality of impingement plates along opposite radial surfaces of the outer circumferential support platform. 14. The method for manufacturing the turbine nozzle assembly of claim 12, further comprising forming in the outer circumferential support platform a plurality of cooling airflow openings that provide a passageway for cooling air to flow from the air flow space into a cooling circuit of the vane. 15. The method for manufacturing the turbine nozzle assembly of claim 12, further comprising forming the plurality of gap-maintaining features along an inner radial surface of each impingement plate of the plurality of impingement plates. 16. The method for manufacturing the turbine nozzle assembly of claim 12, further comprising forming the plurality of gap-maintaining features along an outer radial surface of the outer circumferential support platform. 17. The method for manufacturing the turbine nozzle assembly of claim 12, further comprising forming the plurality of gap-maintaining features as a plurality of hemispherical dimple structures.