Gas turbine can annular combustor

US7080515B2 · kind B2 · utility

Assignee

• Siemens Westinghouse Power Corporation · US

Inventors

• Samer P. Wasif · Oviedo, US
• Udo Schmitz · Wetter (Ruhr), DE
• Robert Bland · Oviedo, US
• Karsten Jordan · Essen, DE
• John Carl Glessner · Kings Mills, US
• J. Scott Markovitz · Sanford, US
• Bernd Prade · Wetter (Ruhr), DE
• David Kargetta · New Smyrna Beach, US
• Stephen A. Ramier · Fredericton, CA
• Stefan Dahlk · Kempten (Allgäu), DE

Key dates

• Filing date: Sep 19, 2003
• Grant date: Jul 25, 2006
• Expiry date: Dec 17, 2023

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F23R2900/03044
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A gas turbine engine (120) includes a cylindrical basket (146) having an axis (14) and a single main burner assembly (12) disposed within the basket. A burner insert (34) is disposed in an annular space between the burner assembly and the basket. The insert includes a face perpendicular to the axis of the basket. A plurality of passageways (114) are formed in the basket, positioned proximate to and downstream of the burner insert for allowing passage of a portion of an oxidizer flow (42) into a combustion chamber (30). A fluid flow path (38), defined between a combustion chamber liner portion (32) of the basket and a casing (40) spaced radially outward from the combustion liner portion, discharges a fluid into a flow reversal region (118) proximate an inlet (20) of the burner assembly. A fuel outlet (44) is disposed in the flow reversal region.