DRIVE AXIAL CENTRIFUGAL BREATHER Russian patent published in 2016 - IPC F02C7/06 

Abstract RU 2588307 C1

FIELD: engines and pumps.

SUBSTANCE: invention relates to elements of breathing system of aircraft gas turbine engine (GTE). Before support bearing is installed through radial hole in shaft lock in form of cylindrical pin so that protruding beyond side surface of shaft cylindrical sections of pin are located in front end of internal shoulder of support bearing fixed relative to body.

EFFECT: end sections of pin are hidden inside made in impeller at input of annular groove, ruling out ingress of destruction elements towards drive mechanism (drive box of propulsion units), which increases reliability of breather design.

1 cl, 2 dwg

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RU 2 588 307 C1

Authors

Golubov Aleksandr Nikolaevich

Semenov Vadim Georgievich

Marchukov Evgenij Yuvenalevich

Dates

2016-06-27Published

2015-03-19Filed