Burner for an aircraft gas turbine engine

A gas turbine engine for an aircraft propulsion system, the gas turbine engine comprising:

• a compressor section configured to form a compressed air;
• and
• at least one burner including:
• a hydrogen manifold;
• an outer nozzle extending circumferentially about an axial centerline to form a combustion chamber within the outer nozzle, the outer nozzle includes an outer converging axial portion, the outer converging axial portion is disposed at an upstream axial end of the outer nozzle, and the upstream axial end is disposed at the hydrogen manifold;
• and
• an inner nozzle extending circumferentially about the axial centerline to form an air passage along the axial centerline, the inner nozzle is connected in fluid communication with the compressor section and configured to direct the compressed air from the compressor section to the combustion chamber through the air passage, and the inner nozzle includes an inner converging axial portion at a downstream axial end of the inner nozzle;
• the outer converging axial portion and the inner converging axial portion form an annular gap, and the outer converging axial portion and the inner converging axial portion are configured to direct a hydrogen fuel from the hydrogen manifold to the combustion chamber through the annular gap.

An assembly for a gas turbine engine, the assembly comprising:

• at least one burner including:
• an outer nozzle extending circumferentially about an axial centerline to form a combustion chamber within the outer nozzle, the outer nozzle includes an outer converging axial portion and an outer diverging axial portion, the outer converging axial portion is disposed at an upstream axial end of the outer nozzle, and the outer diverging axial portion is disposed axially downstream of the outer converging axial portion;
• and
• an inner nozzle extending circumferentially about the axial centerline, the inner nozzle including an inner converging axial portion at a downstream axial end of the inner nozzle;
• the outer converging axial portion and the inner converging axial portion form an annular gap extending along an angle α toward the axial centerline;
• wherein the outer diverging axial portion extends along an average divergence angle Θ between four degrees and seven degrees relative to the axial centerline.