Gas Turbine Engine And Method Of Assembling The Same

Abstract: A method and system for a turbofan gas turbine engine system (100) is provided. The gas turbine engine system (100) includes a variable pitch fan (VPF) assembly (102) coupled to a first rotatable shaft (118) and a low pressure compressor LPC (104) coupled to a second rotatable shaft (120). The LPC (104) including a plurality of variable pitch stator vanes (130) interdigitated with rows of blades (132) of a rotor of the LPC (104). The gas turbine engine system (100) also includes a speed reduction device (128) coupled to said first rotatable shaft (118) and said second rotatable shaft (120). The gas turbine engine system (100) further includes a modulating pressure relief valve (134) positioned between an outlet (136) of said LPC (104) and a bypass duct (138) and a controller (202) configured to schedule a position of said plurality of variable pitch stator vanes (130) and said modulating pressure relief valve (134) in response to an operational state of said turbofan gas turbine engine system (100) and a temperature associated with said LPC (104).

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