Single cavity trapped vortex combustor with CMC inner and outer liners

A combustor assembly, comprising:

• an annular inner liner extending generally along an axial direction, the inner liner including an inner flange extending forward from an upstream end of the inner liner;
• an annular outer liner extending generally along the axial direction;
• and
• a combustor dome extending between the upstream end of the inner liner and an upstream end of the outer liner, the combustor dome including an outer flange extending forward from a radially innermost end of the combustor dome,
• wherein the inner liner, the outer liner, and the combustor dome define a combustion chamber therebetween,
• wherein the combustor dome and a portion of the inner liner together define an annular cavity of the combustion chamber,
• wherein the inner flange and the outer flange define an airflow opening therebetween, and
• wherein the inner flange defines a first protrusion extending radially into the airflow opening, the outer flange defines a second protrusion extending radially into the airflow opening such that the first protrusion and the second protrusion are radially aligned, the first and second protrusions defining an air chute for providing a flow of air to the annular cavity, the first annular cavity adjacent the air chute.

A method for assembling a combustor assembly of a gas turbine engine, comprising:

• inserting an annular inner liner within the gas turbine engine, the inner liner including an inner flange extending forward from an upstream end of the inner liner;
• inserting an annular outer liner within the gas turbine engine, the outer liner circumferentially surrounding the inner liner, the outer liner including an outer flange extending forward from an upstream end of the outer liner, the inner liner and the outer liner defining a combustion chamber therebetween, the combustion chamber having an annular cavity, the inner flange and the outer flange defining an airflow opening therebetween for providing a flow of air to the annular cavity of the combustion chamber, the airflow opening having a width;
• and
• after inserting both the inner liner and the outer liner, positioning a chute member within the airflow opening to define an air chute for generating a vortex of air within the annular cavity, the chute member reducing the width of the airflow opening between the inner flange and the outer flange.