Flow modifying device

US4534166A · kind A · utility

Assignee

• The United States of America as represented by the Administrator of the National Aeronautics and Space Administration · US

Inventors

• James S. Kelm · Milford, US
• Edward Charles Vickers · Cincinnati, US
• Jesse J. Williams · Cincinnati, US
• Jack Roy Taylor · Flint, US

Key dates

• Filing date: Jun 3, 1983
• Grant date: Aug 13, 1985
• Expiry date: Jun 3, 2003

Classification

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

Abstract

A swirler for a gas turbine engine combustor is disclosed for simultaneously controlling combustor flow rate, swirl angle, residence time and fuel-air ratio to provide three regimes of operation. A first regime is provided in which fuel-air ratio is less than stoichiometric, NOx is produced at one level, and combustor flow rate is high. In a second regime, fuel-air ratio is nearly stoichiometric, NOx production is less than that of the first regime, and combustor flow rate is low. In a third regime, used for example at lightoff, fuel-air ratio is greater than stoichiometric and the combustor flow rate is less than in either of the other regimes.