Patent References 2826039 2916878 3919840 Integral refilmer lip for floatwall panels Combustion chamber liner insert Patent #: 4875339 InventorsAssigneeApplicationNo. 659353 filed on 02/19/1991US Classes:60/752, Combustor liner60/759Air scoop extends into air flowing outside linerExaminersPrimary: Bertsch, Richard A.Assistant: Thorpe, Timothy S. Attorney, Agent or FirmForeign Patent References
International ClassF23R 003/04AbstractA gas turbine engine combustor, eg of annular combustor configuration, has air inlets, typically in the dilution zone, which incorporate vortex generators operative to trip the inlet jet flow causing stabilizing vortex flow at the lateral edges of the jet. The vortex generators can comprise an inwardly directed abrupt change of section between forward and rearward parts of the air inlets. The rearward section of the air inlets can have a configuration operative to reinforce the jet stabilizing effect of the vortex flow. The combustor exhibits improved uniformity of jet and crossflow mixing.Field of SearchCombustor linerHaving means to direct flow along inner surface of liner In an axial direction Air scoop extends into air flowing outside liner Air outside liner flows counter to combustion products flow within liner FLAME HOLDER HAVING PROTECTIVE FLAME ENCLOSING OR FLAME STABILIZING STRUCTURE Including means feeding air axially spaced points of the flame Axial perforations along combustion tube | |