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US 2009/0013696 A1Published application
Gas turbine engine mixing duct and method to start the engine
AssigneeRolls-Royce Canada, Ltd.
InventorTomas Scarinci
Life of this patent
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Abstract
A combustion chamber device having a field static pressure gradient adapted to expel a flame kernel or hot spot from a fuel-air mixing duct. The swirling flow passing through an annular mixing duct is turned from a radial direction to an axial direction before entering the combustion chamber. An ignition source located within the fuel-air mixing duct can then be used to start the combustion process in the gas turbine.
Claims10
A method of starting a gas turbine engine, comprising:
- imparting swirl to a fluid including air;
- introducing a fuel into the fluid to form a fuel and air mixture;
- flowing the fuel and air mixture through an annular duct disposed in fluid flow communication with a combustion chamber of the gas turbine engine;
- igniting a portion of the fuel and air mixture within the annular duct to form a hot spot;
- and
- subjecting the hot spot to a pressure gradient within the annular duct to expel the hot spot from the annular duct and into the combustion chamber.
3 more elements
10-22. (canceled)
Dependencies are inferred from the claim text.