EP 0166940 B1 19890329 - RUNNING-IN COATING FOR A TURBOMACHINE
Title (en)
RUNNING-IN COATING FOR A TURBOMACHINE
Publication
Application
Priority
DE 3424661 A 19840705
Abstract (en)
[origin: EP0166940A2] 1. Sintered running-in coating for a turbo-machine, particularly a gas turbine, to reduce the radial clearance between rotor blades and housing, with spherical particles comprising a graphite core and a thin-gauge casing of nickel or a nickel alloy with chromium, aluminium or copper, characterized in that it consists solely of spherical particles which are sintered to form a coating of a densely closed surface.
IPC 1-7
IPC 8 full level
F01D 11/08 (2006.01); B22F 3/11 (2006.01); B22F 7/00 (2006.01); F01D 11/12 (2006.01)
CPC (source: EP US)
B22F 3/1112 (2013.01 - EP US); B22F 7/002 (2013.01 - EP); F01D 11/125 (2013.01 - EP); B22F 2998/10 (2013.01 - EP)
Citation (examination)
DE 2239840 A1 19730524 - UNITED AIRCRAFT CORP
Designated contracting state (EPC)
FR GB IT SE
DOCDB simple family (publication)
EP 0166940 A2 19860108; EP 0166940 A3 19860521; EP 0166940 B1 19890329; DE 3424661 A1 19860116; DE 3424661 C2 19880218; JP H0379523 B2 19911219; JP S6123805 A 19860201
DOCDB simple family (application)
EP 85106255 A 19850522; DE 3424661 A 19840705; JP 14691285 A 19850705