Combustion device and gas turbine

A combustion device comprising:

• a combustor in which a combustion chamber in which fuel is combusted using combustion air is formed wherein
• the combustor includes:
• a reducing agent injector that injects a reducing agent toward flames in the combustion chamber;
• a liner having an internal space used as the combustion chamber;
• a casing accommodating the liner;
• a fuel nozzle configured to inject the fuel into the combustion chamber;
• and
• a flow adjuster which is annularly provided around the fuel nozzle at one end of the casing and is configured to supply the combustion air from one end of the combustion chamber and to form a swirling flow of the combustion air inside the combustion chamber, and
• the reducing agent injector is configured to inject the reducing agent n a direction along the swirling flow formed by the flow adjuster when viewed from a plane perpendicular to a mainstream direction in the combustion chamber.