DESIGN OF GEAR TURBOFAN GAS TURBINE ENGINE Russian patent published in 2017 - IPC F02C7/36 F02C7/06 F02K3/06 

FIELD: engine devices and pumps.

SUBSTANCE: gas turbine engine comprises a fan, a compressor section, a combustion chamber in fluid communication with the compressor section, a turbine section in fluid communication with the combustion chamber, and a speed adjustment system. The turbine section includes a fan drive turbine and the second turbine, where the fan drive turbine comprises of a plurality of turbine stages. The fan comprises of a plurality of blades configured to rotate around the axis. The ratio between the number of fan blades and the number of stages of the fan drive turbine is from 2.5 to 8.5. The speed adjustment system is driven by the fan drive turbine to rotate the fan around the axis. The fan drive turbine comprises of the first rear rotor connected to the first shaft, and the second turbine comprises second rear rotor connected to the second shaft. Between the first shaft and the second shaft, an annular gap is formed. The first bearing assembly is located axially behind the first connection between the first rear rotor and the first shaft and the second bearing assembly is located in the annular gap formed between the first shaft and the second shaft.

EFFECT: invention makes it possible to eliminate the need for load-bearing structures connected to the fixed structure via an intermediate power frame, to reduce the length of the shafts, to support the external shaft coaxially with the coupling of the high-pressure turbine rotor with the outer shaft, to provide a more compact turbine section, and to reduce its weight and fuel consumption.

20 cl, 13 dwg