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.
Patent No.:
Date of Patent:
Aug. 18, 2020
Filed:
May. 31, 2018
Applicant:
Safran Aero Boosters SA, Herstal, BE;
Inventor:
Stéphane Hiernaux, Oupeye, BE;
Assignee:
SAFRAN AERO BOOSTERS SA, Herstal, BE;
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 11/12 (2006.01); F01D 11/00 (2006.01); F04D 19/02 (2006.01); F04D 29/02 (2006.01); F04D 29/16 (2006.01);
U.S. Cl.
CPC ...
F01D 11/001 (2013.01); F01D 11/122 (2013.01); F04D 19/022 (2013.01); F04D 29/023 (2013.01); F04D 29/164 (2013.01); F05D 2220/323 (2013.01); F05D 2230/10 (2013.01); F05D 2230/312 (2013.01); F05D 2230/60 (2013.01); F05D 2240/55 (2013.01); F05D 2300/40 (2013.01); F05D 2300/506 (2013.01);
Abstract
A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.