Mitsubishi Heavy Industries Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Nobuo Sato

Shigemi Mandai

Hitoshi Kawabata

Katsunori Tanaka

Satoshi Tanimura

Ichiro Fukue

Tetsuo Gora

Hiroyuki Nishida

A combustor inner tube 102 or a burner 101 provided on the upstream side of a tail pipe 103 having a straight or substantially straight axis is disposed at an angle with respect to the axis of tail pipe 103, by which a secondary flow is produced in combustion gas. Thereby, low-temperature gas at the outer peripheral portion is mixed with high-temperature gas at the central portion so that the gas temperature distribution is made uniform.

Gas turbine combustor with angled tube section

A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles surround the pilot nozzle. A diverging cone projects from the vicinity of the injection port of the pilot nozzle such that the flame from the main nozzles is sustained by the pilot nozzle and NOx is suppressed. The main nozzles can be provided upstream of the injection port of the pilot nozzle in which case an annular premixing nozzle having a throttled exit end is disposed downstream of the main nozzles. The main nozzle may also be in the form of a fuel nozzle having a plurality of tubes, a gaseous fuel being injected through one of the tubes, and liquid fuel being injected into the annular premixing nozzle through the other of the tubes so that the liquid fuel is atomized to mix the fuel and air homogeneously.

Combustor for gas turbines with diverging pilot nozzle cone

Growing community of inventors

Takasago, Japan

Nobuo Sato