Friction damper for gas turbine engine blades

Fluid reaction surfaces (i.e. – impellers) – Rotor having flow confining or deflecting web – shroud or... – Axially extending shroud ring or casing

Patent

Rate now

  [ 0.00 ] – not rated yet Voters 0   Comments 0

Details

416196R, 416500, F01D 526

Patent

active

055991653

ABSTRACT:
A friction damper (50) provides friction damping for gas turbine engine airfoils to reduce vibrations thereto. The friction damper (50) includes a plate (52) underlying radially outer shrouds (30) of two adjacent airfoils (20). Friction generated between an outer surface (53) of the plate (52) and undersides (42) of the adjacent shrouds (30) reduces undesirable vibrations in the airfoils (20).

REFERENCES:
patent: 2610823 (1952-09-01), Knowlton, Jr.
patent: 2912157 (1959-11-01), Taylor
patent: 3719432 (1973-03-01), Musick et al.
patent: 3986792 (1976-10-01), Warner
patent: 4025232 (1977-03-01), Imai et al.
patent: 4028006 (1977-06-01), Kuroda et al.
patent: 4083655 (1978-04-01), Tempere
patent: 4177011 (1979-12-01), Eskesen et al.
patent: 4721434 (1988-01-01), Marshall et al.
patent: 5156529 (1992-10-01), Ferleger et al.
patent: 5257908 (1993-11-01), Ortolano
patent: 5281097 (1994-01-01), Wilson et al.
patent: 5522705 (1996-06-01), Elaini et al.

LandOfFree

Say what you really think

Search LandOfFree.com for the USA inventors and patents. Rate them and share your experience with other people.

Rating

Friction damper for gas turbine engine blades does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Friction damper for gas turbine engine blades, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Friction damper for gas turbine engine blades will most certainly appreciate the feedback.

Rate now

     

Profile ID: LFUS-PAI-O-673426

  Search
All data on this website is collected from public sources. Our data reflects the most accurate information available at the time of publication.