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US 6,209,325 B1Granted
Combustor for gas- or liquid-fueled turbine
AssigneeEuropean Gas Turbines Limited
InventorHisham S Alkabie
Life of this patent
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Abstract
The combustor has three injection stages to supply fuel or a fuel/air mixture progressively to a pre-chamber or a main combustion chamber wherein the third injection stage comprises an elongated passage with an arrangement for introducing fuel into the passage. Preferably the passage extends alongside the combustion chamber and/or another passage for cooling air.
Claims20
A combustor for a turbine, comprising:
- a) a pre-chamber having a cross-section;
- b) a first injection stage for supplying a first proportion of a combustible along a flow direction to the pre-chamber for combustion therein;
- c) a second injection stage for supplying a second proportion of the combustible to the pre-chamber downstream of the first injection stage for combustion in the pre-chamber;
- d) a main combustion chamber in fluid flow communication with the pre-chamber downstream of the pre-chamber, the main chamber having a cross-section larger than the cross-section of the pre-chamber to define a transition region, the main chamber having a length as considered along the flow direction;
- e) a cooling air passage extending along at least a part of the length of the main chamber and being in a heat-exchanging relationship with the main chamber;
- and
- f) a third injection stage for supplying a third proportion of the combustible to the transition region for combustion in the transition region and in the main chamber, the third injection stage including an injection passage extending along at least a part of the length of the main chamber and being in a heat-exchanging and surrounding relationship with the cooling air passage and, in turn, with the main chamber to heat the third portion of the combustible prior to being supplied to the transition region.
4 more elements
Dependencies are inferred from the claim text.