Patent ID: 8490405

Claim:
A method of combusting a fuel and air mixture in a gas turbine engine, the method comprising: radially inflowing a gas that includes air toward a central axis of a combustion device disposed in the gas turbine engine; swirling the gas using a swirler structure; introducing a fuel into the gas to form a fuel and air mixture; flowing the fuel and air mixture through an annular duct having an end portion disposed in fluid flow communication with a combustion chamber of the gas turbine engine, the combustion chamber located upstream of a turbine of the gas turbine engine; igniting a portion of the fuel and air mixture within the annular duct to form a hot spot upstream of the combustion chamber; and in a location upstream of the turbine in the gas turbine engine, subjecting the hot spot to a pressure gradient within the annular duct to expel the hot spot through the end portion of the annular duct and into the combustion chamber.