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US 8,769,960 B2Granted
Gas turbine engine mixing duct and method to start the engine
AssigneeRolls-Royce Canada, Ltd.
InventorTomas Scarinci
Life of this patent
Estimating the term…
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.
Claims6
An apparatus comprising:
- a housing;
- a centerbody located within said housing;
- a combustion chamber;
- an annular fluid flow passage located within said housing and around at least a portion of said centerbody, said annular fluid flow passageway having an outlet in flow communication with said combustion chamber;
- a plurality of radial vanes located within said housing and adapted to impart swirl to a working fluid flow passing through said annular fluid flow passage;
- and
- wherein said annular fluid flow passage between said plurality of radial vanes and said outlet being a curvilinear passage configured to turn the working fluid flow from a radial inwards direction to an axial direction and the force due to the swirling motion of the working fluid flow is equal and opposite to the force due to turning the working fluid flow from a radial direction to an axial direction.
4 more elements
Dependencies are inferred from the claim text.