GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME

摘要

A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.

主权项

1. A turbofan gas turbine engine system comprising:
a variable pitch fan (VPF) assembly coupled to a first rotatable shaft; a low pressure compressor LPC coupled to a second rotatable shaft, said LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC; a core engine configured in series flow arrangement with said VPF and said LPC; a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft, said speed reduction device configured to drive said first rotatable shaft at a rotational speed that is lower than the rotational speed of the second rotatable shaft; a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct; and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.