Turbofan aircraft engine

US10001083B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Klaus-Peter Rued · Puchheim, DE
• Werner Humhauser · Moosburg an der Isar, DE
• Hermann Klingels · Dachau, DE
• Rudolf Stanka · Rattenkirchen, DE
• Eckart Heinrich · Germering, DE
• Hans-Peter Hackenberg · Olching, DE
• Stefan Weber · Munich, DE
• Claus Riegler · Karlsfeld, DE
• Erich Steinhardt · Munich, DE
• Jochen Gier · Karlsfeld, DE
• Manfred Feldmann · Eichenau, DE
• Norbert Huebner · Dachau, DE
• Karl Maar · Pfaffenhofen an der Ilm, DE

Key dates

• Filing date: Jul 18, 2014
• Grant date: Jun 19, 2018
• Expiry date: Feb 10, 2036

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F02C3/107
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.