Abstract
In a gas turbine engine, a turbine blade vibration damper is located between the underside of a blade platform and a turbine disc, and comprises a member which extends axially parallel to the blade roots. The member has on its outer surface an inverted "V" shaped projection which engages a complementary shaped recess in the underside of the blade platforms. The member has two limbs of unequal length. Centrifugal forces on the longer limb rocks the member and urges the shorter limb into engagement with the disc rim.
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Published version (
Free)
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
