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A turbine blade includes an airfoil, platform, and dovetail. The airfoil includes a plurality of flow channels being separated by partitions. A primary partition includes an inner saddle. And, a bipedal damper includes a pair of legs extending into the flow channels, and integrally joined together

A turbine blade includes an airfoil, platform, and dovetail. The airfoil includes a plurality of flow channels being separated by partitions. A primary partition includes an inner saddle. And, a bipedal damper includes a pair of legs extending into the flow channels, and integrally joined together at a seat bridging the saddle.

대표청구항 ▼

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A turbine blade comprising: an airfoil integrally formed at a root with a platform and mounting dovetail; said airfoil havin

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A turbine blade comprising: an airfoil integrally formed at a root with a platform and mounting dovetail; said airfoil having a plurality of flow channels extending in span from said dovetail to an outer tip thereof, and adjacent channels being separated by a corresponding primary partition having an inner saddle; and a bipedal damper having a pair of legs extending in span into corresponding ones of said channels and integrally joined together at a seat bridging said saddle. 2. A blade according to claim 1 wherein: said airfoil includes opposite pressure and suction sides extending in span between said root and tip, and extending in chord between opposite leading and trailing edges; said primary partition extends in span inside said airfoil and is integrally joined with said pressure and suction sides; said flow channels include a common inlet extending through said platform and dovetail to the inner base thereof; and said damper is slender in span and sized to fit through said dovetail inlet to position said legs into said channels. 3. A blade according to claim 2 wherein: said primary partition is inclined longitudinally inside said airfoil; and said damper includes a first leg conforming with said primary partition and disposed in laterally abutting contact therewith, and a second leg laterally spaced from an opposite side of said primary partition and disposed in laterally abutting contact with a secondary partition. 4. A blade according to claim 3 wherein said secondary partition comprises a plurality of pins extending transversely between said airfoil sides and aligned longitudinally in abutting contact with said damper second leg. 5. A blade according to claim 3 wherein said secondary partition comprises a row of ribs extending transversely between said airfoil sides and aligned longitudinally in abutting contact with said damper second leg. 6. A blade according to claim 3 wherein said secondary partition extends longitudinally through said airfoil and is spaced from said primary partition to define corresponding ones of said flow channels. 7. A blade according to claim 3 wherein said damper seat is disposed adjacent said platform, and said damper legs extend outwardly therefrom through said airfoil greater than about the mid-span thereof. 8. A blade according to claim 3 wherein said damper seat is disposed at said dovetail base, and said damper legs extend outwardly therefrom through said dovetail, platform, and airfoil. 9. A blade according to claim 3 wherein said damper further includes a common stem extending inwardly from said seat to said dovetail base. 10. A blade according to claim 9 wherein said damper further includes a metering plate affixed to said stem and to said dovetail at said inlet. 11. A blade according to claim 9 wherein said damper further includes a stepped block affixed to said stem and to a complementary notched seat inside said inlet at said dovetail base. 12. A blade according to claim 9 wherein said stem is affixed to said dovetail to support said damper seat below said saddle and bypass centrifugal loading of said damper from said saddle to said dovetail. 13. A blade according to claim 3 wherein said damper initiates at one end at said seat thereof and terminates at an opposite end of said legs. 14. A blade according to claim 13 wherein: said damper seat longitudinally abuts said partition saddle for transferring centrifugal loads thereto; and further comprising a retainer abutting said damper seat on an opposite side thereof for trapping said damper against said primary partition. 15. A blade according to claim 14 wherein said retainer comprises a pin extending transversely through the shank of said blade between said platform and dovetail. 16. A blade according to claim 14 wherein said retainer comprises a metering plate affixed to said dovetail at said inlet. 17. A blade according to claim 13 wherein: said saddle is bulbous and wider than said primary partition adjacent thereto; and said damper legs are bowed around said seat, and have a narrower spacing than said bulbous saddle to longitudinally retain said damper on said primary partition. 18. A blade according to claim 17 wherein said damper legs are bowed larger in width than said bulbous saddle to provide lateral voids therebetween. 19. A blade according to claim 17 wherein said damper legs are bowed to conform with said bulbous saddle. 20. A turbine blade comprising: a hollow airfoil including opposite pressure and suction sides extending in span between a root and tip, and extending in chord between opposite leading and trailing edges; a platform and an integral dovetail affixed to said airfoil root; said airfoil further including a plurality of flow channels separated by corresponding partitions and extending in span between said root and tip; said partitions including a primary partition having an inner saddle at an inner end thereof; said flow channels including a common inlet extending through said dovetail and platform to said airfoil; and a bipedal damper having first and second legs extending in span into corresponding ones of said flow channels inside said airfoil, and integrally joined together at an arcuate seat bridging said saddle. 21. A blade according to claim 1 wherein: said partitions include a secondary partition spaced laterally from said primary partition, and both said primary and secondary partitions are inclined longitudinally inside said airfoil; said damper first leg conforms with said primary partition and is disposed in abutting contact therewith; and said damper second leg conforms with said secondary partition and is disposed in abutting contact therewith. 22. A blade according to claim 21 wherein said damper further includes a common stem extending inwardly from said seat to a base of said dovetail. 23. A blade according to claim 22 wherein said damper further includes a metering plate affixed to said stem and to said dovetail at said inlet. 24. A blade according to claim 22 wherein said damper further includes a stepped block affixed to said stem and to a complementary notched seat inside said inlet at said dovetail base. 25. A blade according to claim 22 wherein said stem is affixed to said dovetail to support said damper seat below said saddle and bypass centrifugal loading of said damper from said saddle to said dovetail. 26. A blade according to claim 21 wherein said damper seat is disposed adjacent said platform, and said damper legs extend outwardly therefrom through said airfoil greater than about the mid-span thereof. 27. A blade according to claim 26 wherein: said damper seat longitudinally abuts said partition saddle for transferring centrifugal loads thereto; and further comprising a retainer abutting said damper seat on an opposite side thereof for trapping said damper against said primary partition. 28. A blade according to claim 27 wherein said damper initiates at one end at said seat thereof and terminates at an opposite end of said legs; and said flow channels are unobstructed by said damper between said seat and said common inlet. 29. A blade according to claim 27 wherein said damper legs are bowed around said seat for locally increasing the width of said damper thereat.