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US 7,841,181 B2Granted
Gas turbine engine combustion systems
AssigneeRolls-Royce Power Engineering PLC
InventorsThomas Scarinci, Anthony John Moran, Lynn Ivor Thomas Steward, Bryn Jones
Life of this patent
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Abstract
One embodiment is a unique gas turbine engine combustion chamber including primary and secondary burning zones. Other embodiments include unique gas turbine engine apparatuses, systems, methods, and combinations.
Claims8
A gas turbine engine combustion system comprising:
- a combustion device including
- a combustion chamber including a primary combustion zone and a secondary combustion zone,
- a centerbody extending into the combustion chamber,
- the primary combustion zone surrounding the centerbody at a location upstream from the secondary combustion zone,
- a first air and fuel discharge adapted for delivering a first premixed air and fuel charge into the primary combustion zone, and
- a second air and fuel discharge adapted for delivering a second premixed air and fuel charge into the secondary combustion zone;
- wherein the first air and fuel discharge includes an annular mixing duct leading to an annular opening surrounding the centerbody and outputting to the primary combustion zone,
- the second air and fuel discharge includes an annular mixing duct leading to an annular opening at a downstream end of centerbody outputting to the secondary combustion zone, and
- a primary combustion process in the primary combustion zone is substantially completed prior to the second fuel and air discharge.
6 more elements
Dependencies are inferred from the claim text.