Patent attributes
A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a drive shaft; a booster compressor positioned downstream of the fan section including a plurality of stages, where each stage includes a stationary compressor blade row and a rotating compressor blade row connected to the drive shaft and interdigitated with the stationary compressor blade row; and, a combustion system for producing pulses of gas having increased pressure and temperature of a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet. A first source of compressed air from the booster compressor is provided to the combustion system inlet and a second source of compressed air from the booster compressor is provided to cool the combustion system, where the pressure of the compressed air from the second source has a greater pressure than that of the compressed air from the first source.
