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:
May. 01, 2018

Filed:

May. 15, 2013
Applicant:

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

Inventor:

Vasiliki Iliopoulou, Winksele, BE;

Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F04D 29/38 (2006.01); F04D 29/54 (2006.01); F01D 5/14 (2006.01); F04D 29/32 (2006.01);
U.S. Cl.
CPC ...
F04D 29/384 (2013.01); F01D 5/141 (2013.01); F04D 29/324 (2013.01); F04D 29/544 (2013.01); F05D 2250/38 (2013.01); F05D 2250/70 (2013.01); F05D 2250/75 (2013.01); Y02T 50/673 (2013.01);
Abstract

The present disclosure provides a subsonic rotor and/or stator blade profile of an axial turbomachine compressor, such as a turbojet. The blade comprises a leading edge with an S-shaped lateral profile in its mid-plane. Specifically, the profile includes, from its inner end to the outer end, a first convex portion including the foremost point of the blade, and a second concave portion including the rearmost area of the blade. This profile enables the fluid flow between 20% and 80% of the blade's length to be redistributed. This so-called 'sweep' profile increases the performance of the stage with such blades because it reduces blade tip vortex losses as well as secondary losses.


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