ApplicationNo. 659353 filed on 02/19/1991
US Classes:60/752, Combustor liner60/759Air scoop extends into air flowing outside liner
ExaminersPrimary: Bertsch, Richard A.
Assistant: Thorpe, Timothy S.
Attorney, Agent or Firm
Foreign Patent References
International ClassF23R 003/04
AbstractA 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 liner
Having 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