Patent ID: 6648592
Filing Date: 2003-11-18
Classification: F01D,F04D,Y02T

Abstract:
A centripetal-flow airbleed system for a gas-turbine engine having a compressor including first and second disks comprising:an annular support affixed to said first and second disks and having a plurality of peripherally spaced orifices defined along the radius thereof; a plurality of airbleed tubes each mounted in a substantially radial manner in one of said orifices of said annular support; and a vibration reducing device including a plurality of damping tubes each mounted in one of said orifices of said annular support and enclosing a radially outer portion of a respective one of said airbleed tubes, a radially inner end of said damping tube enclosing a portion of said airbleed tube and delimiting an annular space defined therebetween.