公开(公告)号：US20240360767A1

公开(公告)日：2024-10-31

申请号：US18687378

申请日：2022-08-31

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jean-Hilaire LEXILUS

IPC: F01D5/22

CPC classification number: F01D5/22 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2260/96

Abstract: A damper for an impeller of an aircraft turbomachine includes an elastic member housed in two metallic half-shells so as to allow a relative movement of the half-shells relative to one another.

公开(公告)号：US20240110482A1

公开(公告)日：2024-04-04

申请号：US18264969

申请日：2022-02-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jean-Hilaire LEXILUS ,  Cédric Nicolas BOT ,  Patrick Jean-Louis REGHEZZA

IPC: F01D5/02 ,  B23P6/00 ,  F01D5/30

CPC classification number: F01D5/027 ,  B23P6/002 ,  F01D5/02 ,  F01D5/30 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/20

Abstract: A method for repairing an end plate of a turbomachine rotor, the end plate including a crown having at least two collar fastening holes and at least one balancing-weight fastening hole located between the two collar fastening holes, each collar fastening hole being equipped with a crimped nut, the crown having a damaged portion between two collar fastening holes, the method including the steps of removing the two crimped nuts located on either side of the damage; removing the damaged crown portion, for example by machining; putting in place a strip in the form of a crown portion closing off the removed crown portion, the strip having at least one balancing-weight fastening hole and two mounting holes; fastening the strip to the crown with two crimped nuts, which penetrate the mounting holes, by crimping each nut in a collar fastening hole.