Patent · US Active

Gas turbine axial compressor

US10208765B2 · kind B2 · utility

3Cited by

5References

6Claims

0Family size

Assignee

MTU Aero Engines AG · DE

Inventors

Tobias Froebel · Höhenkirchen-Siegertsbrunn, DE
Sebastian Mann · Munich, DE
Nina Wolfrum · Straubing, DE
Sergio Elorza Gomez · Munich, DE

Key dates

Filing date	Jan 19, 2016
Grant date	Feb 19, 2019
Priority date	—
Expiry date	May 29, 2037

Classification

Technology area (CPC Y)Emerging Cross-Sectional Technologies
CPC primaryY02T50/60
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

The present invention relates to an axial compressor for a gas turbine, in particular an aircraft engine, having at least one rotor blade or guide vane having a blade or vane element, which is arranged in a flow duct, and a leading edge and a trailing edge, which are joined to each other through a pressure side and a suction side, wherein, a new and novel profile section of the blade or vane element is provided.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.