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.
Patent No.:
Date of Patent:
Jul. 29, 2003
Filed:
Aug. 20, 2001
Ephraim Gutmark, Baton Rouge, LA (US);
Christian Oliver Paschereit, Baden, CH;
Wolfgang Weisenstein, Remetschwil, CH;
Alstom (Switzerland) Ltd, Baden, CH;
Abstract
The subject of the invention is a method as well as an apparatus for suppressing flow vortices within a turbo power machine with a premix burner, into which fuel and air are introduced for mixing, which then leave the burner downstream along its burner axis in the form of a fuel/air mixture through a burner outlet and flow into a combustor located downstream from the burner in the flow direction of the fuel/air mixture. The invention is based on the basic idea of—for the fluid-mechanical stabilization of a premix burner, into which at least one combustion air stream ( ) is fed tangentially into a burner chamber ( ) and is mixed with an injected gaseous and/or liquid fuel ( ) while forming a swirl flow ( ) oriented coaxially to the burner axis and induces a reverse flow zone ( ) at a change in the cross-section on a burner mouth ( ), that is used during the operation of the burner to stabilize the flame—increasingly, radially deforming the swirl flow ( ) within the burner chamber ( ) in the direction of the burner mouth ( ) and let it enter the combustor ( ) in a non-rotation-symmetrical flow cross-section, whereby this deformation is created by reducing the free flow cross-section ( ) of the burner chamber ( ). The fuel/air mixture flows into the combustor with a non-rotation-symmetrical flow cross-section.