Burner with atomizer nozzle

US6244051A · kind A · utility

Inventors

• Nikolaos Zarzalis · Dachau, DE
• Thomas Ripplinger · Karlsruhe, DE
• Bernhard Glaeber · Bocholt, DE
• Burkhard Simon · Weingarten, DE

Key dates

• Filing date: Jan 11, 1999
• Grant date: Jun 12, 2001
• Expiry date: Jan 11, 2019

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F23D2900/11101
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

The invention relates to a burner for combustors of gas turbines, the burner having an atomizer nozzle for atomisation of fuel in the combustion air and having a primary and secondary flow channel. In the burners, mostly used in aircraft engines, an extensively homogenous distribution of the air-fuel mixture is to be achieved in the combustor to reduce emissions. The flow channels opening into the combustor are separated from a first component arranged concentrically in relation to the burner axis and having a sleeve-shaped atomizer lip extending cylindrically or conically, and the external secondary flow channel is bounded externally and radially by a second annular component arranged concentrically and having an internal wall extending to converge and diverge. The second component forms an area with the most narrow flow cross-section, and the first component is arranged radially inwards and ends with the atomizer lip at the axial height of the cross-section or upstream thereof. The air flow flows through the flow channels to twist in the same direction. By positioning the atomizer lip at the narrowest flow cross-section in the or just in front of the atomizer nozzle, the fuel can…