Gas turbine stage

US9617863B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Inga Mahle · Munich, DE
• Norbert Huebner · Dachau, DE
• Rudolf Stanka · Rattenkirchen, DE
• Gottfried Schuetz · Munich, DE
• Norman Cleesattel · Zorneding, DE

Key dates

• Filing date: Jul 8, 2014
• Grant date: Apr 11, 2017
• Expiry date: Jul 20, 2035

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A gas turbine stage including a rotor blade array having a plurality of rotor blades and an adjacent stator vane array having a plurality of stator vanes which have leading edges facing the rotor blade array. In a first radial position of a rear face of the rotor blade array, a minimum axial gap is formed between this rear face and an opposite first contact region a stator vane leading edges, and in a second radial position of the rear face different from the first position, the minimum axial gap is formed between the rear face and an opposite second contact region. Between the first and second contact regions, this stator vane leading edge has an axial offset of no more than 0.6% of a radial height of the stator vane leading edge.