Abstract: A combustor is configured such that an outer liner defines a combustion chamber configured such that fuel and air are supplied thereto from an upstream end side, the fuel is subjected to combustion, and a combustion gas flows out to a downstream end side, an inner liner extends to be concentric with the outer liner inside the outer liner, a sub burner is defined between the outer liner and the inner liner, a main burner is defined on the downstream end side, the fuel is supplied at an equivalence ratio and is subjected to combustion in the sub burner, and the fuel and the air are supplied to the main burner through a region provided radially inward of the inner liner and are subjected to combustion while being mixed with a burnt gas.

Abstract: Techniques suitable for recovering energy from a high-temperature gas of an ordinary pressure are provided. A turbomachine has a turbine 16 and compressors 20 and 24. A combustor 12 is disposed at a stage above the turbine 16. A power generating system generates power by passing a working fluid for the turbomachine through the combustor 12, the turbine 16 and the compressors 20 and 24 in that order.

Abstract: Techniques suitable for recovering energy from a high-temperature gas of an ordinary pressure are provided. A turbomachine has a turbine 16 and compressors 20 and 24. A combustor 12 is disposed at a stage above the turbine 16. A power generating system generates power by passing a working fluid for the turbomachine through the combustor 12, the turbine 16 and the compressors 20 and 24 in that order.