Reverse-flow annular combustor for reduced emissions

A combustor for a gas turbine engine, comprising:

• an annular inner liner;
• an annular outer liner circumscribing the annular inner liner;
• and
• a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner;
• wherein the combustion chamber accommodates fluid flow through the annular inner and annular outer liners;
• wherein the combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber;
• wherein the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.

A combustor for a gas turbine engine with an engine centerline, comprising:

• an inner liner;
• an outer liner circumscribing the inner liner;
• a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner, the combustor dome forming a combustion chamber with the inner liner and the outer liner;
• and
• a fuel injector coupled to the outer liner and configured to inject a stream of fuel into the combustion chamber in a tangential direction relative to the engine centerline;
• wherein the combustion chamber comprises a primary zone and a secondary zone to support combustion of fuel and fluid flow through the inner liner and the outer liner;
• and
• wherein a passage height in the primary zone converges to reduce a radial distance between the inner liner and the outer liner.