Damper cooled turbine blade

Details Damper cooled turbine blade Damper cooled turbine blade

2008-01-29

2008-01-29

Look, Edward K. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Rotor having flow confining or deflecting web, shroud or...

Axially extending shroud ring or casing

C415S115000, C416S500000

Reexamination Certificate

active

07322797

ABSTRACT:
A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to sealingly close the chamber across the portal.

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GE Aircraft Engines, “CF6-80C2 HPT Stage 2 Blade,” on sale and in public use in US more than one year before Oct. 31, 2005.
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U.S. Appl. No. 10/903,414, filed Jul. 30, 2004, S. Keith et al.
U.S. Appl. No. 10/909,199, filed Jul. 30, 2004, S. Keith et al.
U.S. Appl. No. 10/903,634, filed Jul. 30, 2004, S. Keith et al.

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