Patent ID: 11920791
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 17:
18. A gas turbine comprising:
a compressor section;
a turbine section; and
a trapped vortex reverse flow combustor arranged between the compressor section and the turbine section, the trapped vortex reverse flow combustor including:
a first dome structure including an outer dome portion, an inner dome portion, and a plurality of first-dome vortex driver airflow openings through the outer dome portion;
a forward outer liner extending downstream from an outer end of the first dome structure;
an inner liner extending downstream from an inner end of the first dome structure;
a second dome structure extending inward from a downstream end of the forward outer liner, the second dome structure including a plurality of second-dome vortex driver airflow openings arranged at an outer end of the second dome structure, and a plurality of primary driver airflow openings arranged at an inner end of the second dome structure; and
an aft outer liner extending downstream from an inner end of the second dome structure,

wherein (a) a trapped vortex cavity is defined by the outer dome portion, the forward outer liner, and the second dome structure, (b) the plurality of the second-dome vortex driver airflow openings providing a first vortex generating outer airflow therethrough to the trapped vortex cavity, (c) the plurality of the first-dome vortex driver airflow openings providing a first vortex generating mid airflow therethrough radially inward of the first vortex generating outer airflow, the first vortex generating mid airflow and the first vortex generating outer airflow generating a first trapped vortex flow within the trapped vortex cavity, and (d) the plurality of the primary driver airflow openings providing a primary driver airflow therethrough radially inward of the trapped vortex cavity, and (e) the first dome structure, the forward outer liner, the second dome structure, the aft outer liner, and the inner liner define a reverse flow combustion chamber therewithin that reverses a flow direction of the primary driver airflow through the reverse flow combustion chamber, and
wherein the inner liner includes a plurality of inner liner airflow openings providing a secondary driver airflow therethrough, the primary driver airflow and the secondary driver airflow generating a secondary combustion zone vortex flow in a secondary combustion zone defined radially inward of the trapped vortex cavity.