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US 2005/0028526 A1Published application
Burner for a gas-turbine combustion chamber
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorRalf Sebastian Von Der Bank
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AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorRalf Sebastian Von Der Bank
Estimating the term…
On a burner for a gas-turbine combustion chamber which comprises a lean premix burner with centrally integrated stabilizing burner, a core air annulus (11) accommodating the atomizer nozzle (10) of the stabilizing burner is concentrically surrounded by a main air annulus (4) supplying the weak air-fuel mixture. In the adjacent issuing areas of the main air annulus and the core air annulus, a flame stabilization ring (13), which is heated by the combustion gases and whose cross-sectional surface increases in area toward the combustion chamber (5), is provided to produce an approximately hollow-cylindrical hot-gas recirculation zone (17) originating at the flame stabilization ring which ensures a stable flame formation throughout the range of operating conditions of the gas turbine.
A burner for a gas-turbine combustion chamber which comprises a lean premix burner with centrally integrated stabilizing burner, where a core air annulus accommodating an atomizer nozzle of the stabilizing burner is surrounded by a main air annulus of the lean premix burner supplying a weak air-fuel mixture, wherein, in the adjacent issuing areas of the core air and the main air annulus, a flame stabilization ring is positioned which has an inwardly directed core air deflector flank and an outwardly directed main air deflector flank for the formation of a steady, approximately hollow-cylindrical, hot recirculation zone which originates at the flame stabilization ring.
Dependencies are inferred from the claim text.