Gas turbine combustor

US5490378A · kind A · utility

Assignee

• MTU Motoren-und Turbinen-Union München GmbH · DE

Inventors

• Johann Berger · Alfdorf, DE
• Burkhard Simon · Weingarten, DE

Key dates

• Filing date: Dec 7, 1993
• Grant date: Feb 13, 1996
• Expiry date: Dec 7, 2013

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05B2250/411
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A gas turbine combustor has at least one fuel nozzle located at a head end of the combustor. At least one swirl device is adjustable as a function of a load for supplying combustion air. The swirl device includes radial/tangential apertures formed between profiles of an annular body arranged coaxially with respect to the nozzle. The apertures are uniformly distributed around the circumference of the annular body and have aperture cross-sections that are constant along their entire length. The swirl device further includes a sleeve having fingers which extend inwardly to engage the apertures. The sleeve is adjustable with respect to the annular body. The fingers are axially displaceable within the apertures via the sleeve. The fingers are each arranged parallel to aperture walls spaced from the fingers to bound a maximal adjusting path of the fingers to form duct walls of the apertures. The fingers are coordinated with respect to their width and length with the apertures such that in an intermediate adjusted position of the fingers, each finger coordinates with its respective aperture wall to provide a flow cross-section that is constant along the aperture length.