Engine with pressure gain combustor and compressor discharge turbine cooling

A gas turbine engine comprising:

• a compressor including at least one compressor rotor with a compressor blade configured to compress air drawn into the gas turbine engine upon rotation of the compressor rotor,
• a rotating detonation combustor arranged around a reference axis, the rotating detonation combustor including a combustion chamber and an inlet splitter fluidly coupled to the compressor to receive compressed air from the compressor and to the combustion chamber, the rotating detonation combustor configured to mix fuel with compressed air in the combustion chamber, ignite the mixed fuel and compressed air in the combustion chamber, and to discharge products of the combustion reaction between the mixed fuel and the compressed air at a discharge pressure greater than an inlet pressure of the compressed air received from the compressor,
• a turbine system that defines a flow path across which static vanes and rotating blades extend, the flow path fluidly coupled to the rotating detonation combustor so as to receive products of the combustion reaction from the rotating detonation combustor, and the static vanes and rotating blades formed to include cooling air passageways shaped to carry cooling air therethrough to lower the temperature of the associated static vanes and rotating blades,
• wherein the inlet splitter of the rotating detonation combustor is shaped to include a combustion passageway that fluidly couples the compressor with the combustion chamber and a bypass passageway separated from the combustion chamber that fluidly couples the compressor with the cooling air passageways formed in the static vanes and rotating blades, and
• wherein the compressor includes a compressor airfoil upstream of the inlet splitter of the rotating detonation combustor, and
• wherein the compressor airfoil has a combustor portion upstream of the combustion passageway shaped to compress air directed to the combustion passageway and a bypass portion shaped to compress air directed to the bypass passageway, and
• wherein the bypass portion of the compressor airfoil is shaped to increase pressure of compressed air directed to the bypass passageway more than the combustor portion of the compressor airfoil.