Patent ID: 7540707
Filing Date: 2009-06-02
Classification: F01D,F16L,Y02T

Abstract:
1. A link device between an enclosure configured to pass cooling air and a stator nozzle in a turbomachine such as an airplane turbojet, the device comprising: metal tubes with ends mounted to slide in a leaktight manner in orifices in a casing of the enclosure and in orifices in the stator nozzle, a first end of each tube being engaged in a ring having a radially outer collar that is slidable between first and second guide surfaces that extend perpendicularly to an axis of the orifices and that are carried by said nozzle, wherein the first guide surface is situated beside the casing and is held stationary relative to the nozzle, and the second guide surface is movable axially relative to the nozzle and is disposed on a member abutting return means configured to urge said second guide surface towards the casing.