PURPOSE: To obtain a combustion apparatus for a gas turbine having a first stage burner which has excellent stability and easy cooling by injecting mixed gas of fuel and the air as a swirling flow from the burner and forming a diffusion flame by the burner.
CONSTITUTION: A first stage burner 1 is provided near a central axis of a primary combustion chamber 19, and a ringlike second stage burner 2 is provided at a downstream of the chamber 19. The air fed to the burner 1 is mixed with fuel for primary premixing combustion to be injected from a primary premixing combustion fuel injection port 11 in a mixing chamber 6, and injected as a swirling flow into the chamber 19 via a swirler 8 to form a circulation flow 23 at a center of the swirling flow. A diffusion combustion fuel injection port 10 is provided at a center of the burner 1 to inject fuel into the flow 23. At the time of starting a gas turbine, fuel is injected from the port 10 to form a stable diffusion flame.
KOBAYASHI YOSHINOBU
MURAKAMI TADATAKA
ITO KAZUYUKI
AZUHATA SHIGERU
KURODA MICHIO
