General Electric Company
Turbine Engine With Rotating Detonation Combustion System

Abstract:

A turbine engine including a compressor rotor and a rotating detonation combustion (RDC) system. The compressor rotor includes a compressor airfoil defining a trailing edge disposed within a core flowpath of the turbine engine. The core flowpath defines a radial distance between an outer radius and an inner radius at the compressor rotor. The RDC system includes an outer wall and an inner wall each extended along a lengthwise direction and defining a detonation chamber therebetween. The RDC system further includes a strut defining a nozzle assembly and a fuel injection opening providing a flow of fuel to the detonation chamber. The compressor rotor provides a flow of oxidizer in direct fluid communication to the nozzle assembly of the RDC system.