The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Apr. 30, 2019

Filed:

Jun. 30, 2016
Applicant:

Techspace Aero S.a., Herstal (Milmort), BE;

Inventor:

Stéphane Hiernaux, Heers, BE;

Assignee:

SAFRAN AERO BOOSTERS SA, Herstal (Milmort), BE;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 11/00 (2006.01); F01D 11/04 (2006.01); F04D 27/00 (2006.01); F04D 29/08 (2006.01); F04D 29/16 (2006.01); F04D 29/32 (2006.01); F04D 29/52 (2006.01); F04D 29/54 (2006.01); F04D 29/68 (2006.01); F01D 5/06 (2006.01); F02C 6/08 (2006.01);
U.S. Cl.
CPC ...
F04D 29/682 (2013.01); F01D 5/06 (2013.01); F01D 11/001 (2013.01); F01D 11/04 (2013.01); F02C 6/08 (2013.01); F04D 27/009 (2013.01); F04D 29/083 (2013.01); F04D 29/164 (2013.01); F04D 29/321 (2013.01); F04D 29/522 (2013.01); F04D 29/542 (2013.01); F05D 2260/6022 (2013.01); Y02T 50/672 (2013.01);
Abstract

A rotor, in particular a drum of a low-pressure compressor of a turbojet aero engine, is disclosed. The rotor includes an outer annular wall delimiting a primary annular flow of the turbine engine, sealing devices with two rubbing strips or annular ribs formed on the wall. The rubbing strips cooperate by abrasion with inner shrouds. In addition, the annular wall includes rows of intake orifices for leakages which are arranged between each pair of rubbing strips in order to aspirate the recirculation leakages there. A plenum for leakages is formed inside the rotor by means of a composite partitioning, then evacuates the parasitic flow downstream of the turbine engine via the central shaft.


Find Patent Forward Citations

Loading…