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:
Oct. 22, 2019

Filed:

Sep. 06, 2016
Applicant:

Mtu Aero Engines Ag, Munich, DE;

Inventors:

Andreas Hartung, Munich, DE;

Karl-Hermann Richter, Markt Indersdorf, DE;

Herbert Hanrieder, Hohenkammer, DE;

Manfred Schill, Munich, DE;

Assignee:

MTU Aero Engines AG, Munich, DE;

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 9/04 (2006.01); F04D 29/32 (2006.01); F04D 29/66 (2006.01); F01D 5/16 (2006.01); F01D 25/06 (2006.01); F01D 5/26 (2006.01); F04D 29/54 (2006.01);
U.S. Cl.
CPC ...
F04D 29/668 (2013.01); F01D 5/16 (2013.01); F01D 5/26 (2013.01); F01D 9/041 (2013.01); F01D 25/06 (2013.01); F04D 29/324 (2013.01); F04D 29/542 (2013.01); Y02T 50/671 (2013.01);
Abstract

A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber () in which at least one impulse element () is disposed with play, at least one second impact chamber () whose volumetric centroid is offset from a volumetric centroid of the first impact chamber () along a first matrix axis (A) and in which at least one impulse element () is disposed with play, and at least one third impact chamber () whose volumetric centroid is offset from the volumetric centroid of the first impact chamber () along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element () is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.


Find Patent Forward Citations

Loading…