A booster or LP compressor in a twin spool turbofan:
Refer to figure.
The multi-spool layout of a gas turbine engine allows the low-pressure compressor or the fan to handle a large mass flow, a proportion of which is fed into the subsequent compressors while the remainder is ducted to the rear of the engine. This reduces the specific fuel consumption over the normal axial-flow turbojet as about 70-80% of the total thrust is generated by the fan. The low pressor compressor-turbine assembly consists of the LP compressor, a fan drive gear system, an LP shaft, and an LP turbine. The LP compressor consists of a fan and several compressor stages, and it is linked to the LP turbine by the LP shaft. The fan drive gear system is a simple planetary gear reduction unit that connects the fan rotor to the LP compressor which will make them both rotate at the same speed.
The multi-spool layout of a gas turbine engine allows the low-pressure compressor or the fan to handle a large mass flow, a proportion of which is fed into the subsequent compressors while the remainder is ducted to the rear of the engine. This reduces the specific fuel consumption over the normal axial-flow turbojet as about 70-80% of the total thrust is generated by the fan. The low pressor compressor-turbine assembly consists of the LP compressor, a fan drive gear system, an LP shaft, and an LP turbine. The LP compressor consists of a fan and several compressor stages, and it is linked to the LP turbine by the LP shaft. The fan drive gear system is a simple planetary gear reduction unit that connects the fan rotor to the LP compressor which will make them both rotate at the same speed.
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