Tangential bulk swirl air in a trapped vortex combustor for a gas turbine engine

US10823422B2 · kind B2 · utility

Assignee

• General Electric Company · US

Inventors

• Arthur Wesley Johnson · Cincinnati, US
• Joseph Zelina · Waynesville, US
• Eric John Stevens · Mason, US
• Clayton Stuart Cooper · Loveland, US
• Beverly Stephenson Duncan · Sharonville, US
• Juntao Zhang · Dalian, CN

Key dates

• Filing date: Oct 17, 2017
• Grant date: Nov 3, 2020
• Expiry date: Jun 6, 2038

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A trapped vortex combustor for use in a gas turbine engine defines a radial direction, an axial direction, and a circumferential direction. The trapped vortex combustor includes an outer vortex chamber wall defining a forward end, and a dome attached to, or formed integrally with, the outer vortex chamber wall at the forward end of the outer vortex chamber wall. The dome and outer vortex chamber wall define at least in part a combustion chamber having an outer trapped vortex chamber. The dome includes an air chute defining an airflow direction. The radial direction and axial direction of the trapped vortex combustor define a reference plane extending through the air chute, the airflow direction of the air chute defining an angle greater than zero with the reference plane.