| http://www.w3.org/ns/prov#value | - A combustor for a gas turbine engine, comprising:(a) a burner defining an axial fluid-flow path between upstream and downstream ends thereof, said burner including a first portion having a constant cross-sectional area and defining a first combustion zone proximate said upstream end, a second portion having constant cross-sectional area greater than said first area and defining a second combustion
|
