摘要 |
A gas turbine engine (44) having a longitudinal centerline axis (12) therethrough, including: a fan section (16) at a forward end of the gas turbine engine (44 ) including at least a first fan blade row connected to a drive shaft (40/62); a booster compressor (20) positioned downstream of the fan section (16) 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 (40/60) and interdigitated with the stationary compressor blade row; and, a combustion system (46) for producing pulses of gas having increased pressure and temperature of a fluid flow (52) provid ed to an inlet (54) thereof. A first source (64) of compressed air (52) from the booster compressor (20) is provided to the combustion system inlet (54) and a second source (66) of compressed air (65) from the booster compressor (20) is provided to cool the combustion system (46), where the pressure of the compressed air (65) from t he second source (66) has a greater pressure than that of the compressed air (5 2) from the first source (64).
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