Combustion device and gas turbine

A combustion device configured to burn fuel ammonia with combustion air in a combustion chamber, the combustion device comprising:

• a combustor liner which forms the combustion chamber;
• a burner which is installed at one end of the combustor liner, and is configured to supply a fuel having a flame temperature higher than that of the fuel ammonia into the combustion chamber to generate a combustion gas;
• a deflection member which is provided on a downstream side of the combustor liner in a flow direction of the combustion gas, and is configured to deflect the flow direction of the combustion gas;
• and
• at least one ammonia injection hole which is provided in the combustor liner between the burner and the deflection member and is configured to supply the fuel ammonia into the combustion chamber so as to form an ammonia combustion field that pushes away the combustion gas,
• wherein the at least one ammonia injection hole is configured to supply the fuel ammonia toward a part of an inner wall surface of the combustor liner facing the at least one ammonia injection hole such that a cross section of the combustor liner after the fule ammonia is injected from the at least one ammonia injection hole has a biased temperature distribution in which a high temperature portion is formed by the combustion gas pushed away by the ammonia combustion field, and a low temperature portion formed by the ammonia combustion field are present.